Journey of Mangalyaan
38
Journey of Mangalyaan India's First (MOM) M ars O rbiter M ission PRESENTED BY CH.PURUSHOTHAM Aero S CIENCE OF A ERONAUTICS AND E NGINEERING E DUCATION T ECHNICS Department of Aeronautical Engg. 1
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Transcript of Journey of Mangalyaan
1
Journey of Mangalyaan Indias First (MOM) Mars Orbiter Mission
PRESENTED BYCHPURUSHOTHAM
Aero
SCIENCE OF AERONAUTICSAND
ENGINEERING EDUCATION TECHNICS
Department of Aeronautical Engg
2
CONTENTSMARS INTRODUCTIONWHY THIS JOURNEY MISSION PLANMISSION OBJECTIVES
-TECHNOLOGICAL OBJECTIVES- SCIENTIFIC OBJECTIVES
LAUNCH -PSLV XL C25
SPACECRAFTPAYLOADS
-LYMAN ALPHA PHOTOMETER (LAP)-METHANE SENSER FOR MARS (MSM)-MARS EXOSPHERIC NEUTRAL COMPOSITION ANALYSER (MENCA)-THERMAL INFRARED IMAGING SPECTROMETER (TIS)-MARS COLOR CAMERA (MCC)
MISSION PHASES or TRAJECTORY-GEOCENTRIC PHASES-HELIOCENTRIC PHASES-MARTIAN PHASES
14 BRAINS BEHIND THE SUCCESSCOST EFFECTIVENESS COMPARE WITH OTHERE MISSION
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
3
Mars Introduction
Mars is the fourth planet from the Sun and is commonly referred to as the Red Planet The rocks soil and sky have a red or pink hue The distinct red color was observed by stargazers throughout history It was given its name by the Romans in honor of their god of war
Mars is the fourth planet from the sun and the second smallest planet in the solar system after Mercury Named after the Roman god of war it is often described as the ldquoRed Planet because the iron oxide prevalent on its surface gives it a reddish appearance
4
bull Mars is the fourth planet from the sunbull Mars is the seventh largest planet in our solar systembull Mars is referred to as the Red Planet due to its red soil made up of iron oxide
more commonly known as rustbull Mars is named after the Roman god of warbull The equatorial Diameter of Mars is 6805 kmbull The polar diameter of Mars is 6755 kmbull The Diameter of Mars is 6794 kmbull Martian day = 24 hours 34 minutes and 22 secondsbull Martian year = 687 Earth daysbull The mass of Mars is 641850000000000000000000 kgbull Surface temperature on Mars can range from the maximum of 310 K to a
minimum of 150 Kbull Atmospheric components on Mars consists of 9532 carbon dioxide 27
nitrogen 16 argon 013 oxygenbull Average Surface Temperature218K (-53ordm C)bull Average Distance from Sun2279 x 108 kmbull Average Density3934 kgm3
5
bull Moons of Mars = 21 Phobos ndash Diameter 22 km orbit 5981 km from the surface of Mars2 Deimos - Diameter 12 km orbit 20062 km form the surface of Mars
bull Mars atmospheric pressure at surface = 635 mbar gt 100th Earthrsquos atmospheric pressure
6
EarthMars Comparison
Distance from Sun 2279 x 108 km 1496 Million kmDiameter 6794 km 12742 kmLength of Year 687 Earth Days 36525 Days
Length of Day 24 hours 34 minutes and 22 sec
23 hours 56 minutes and 41 sec
Gravity 0375 that of Earth 266 times that of Mars
Temperature 218K (-53ordm C) 14degC
Temperature Range -127 ordm C to 17ordm C -88 ordm C to 58 ordm C Number of Moons 2 1
Mars Earth
7
8
Why this Journey
In an interview with The Hindu Radhakrishnan to a question on whatrsquos the most interesting on Mars he replies saying Life So we talk about Methanewhich is of biological origin or geological origin So we have a methane sensor plus a thermal infrared spectrometer These two together should be able to give some information He went on to say that ldquoWe want to look at environment of Mars for various elements like Deuterium-Hydrogen ratio We also want to look at other constituents mdash neutral constituent
After the EarthIts soil contains water to extractIt isnrsquot too cold or too hot There is enough sunlight to use solar panels Gravity 13 or 38 our Earths be sufficient for the human body to adapt Human speculationThe daynight a Mars day is 24 hours 39 minutes and 35 seconds 687 Days yearPlanet similar to earthextraterrestrial lifescientists to expect life on Mars
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
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- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
2
CONTENTSMARS INTRODUCTIONWHY THIS JOURNEY MISSION PLANMISSION OBJECTIVES
-TECHNOLOGICAL OBJECTIVES- SCIENTIFIC OBJECTIVES
LAUNCH -PSLV XL C25
SPACECRAFTPAYLOADS
-LYMAN ALPHA PHOTOMETER (LAP)-METHANE SENSER FOR MARS (MSM)-MARS EXOSPHERIC NEUTRAL COMPOSITION ANALYSER (MENCA)-THERMAL INFRARED IMAGING SPECTROMETER (TIS)-MARS COLOR CAMERA (MCC)
MISSION PHASES or TRAJECTORY-GEOCENTRIC PHASES-HELIOCENTRIC PHASES-MARTIAN PHASES
14 BRAINS BEHIND THE SUCCESSCOST EFFECTIVENESS COMPARE WITH OTHERE MISSION
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
3
Mars Introduction
Mars is the fourth planet from the Sun and is commonly referred to as the Red Planet The rocks soil and sky have a red or pink hue The distinct red color was observed by stargazers throughout history It was given its name by the Romans in honor of their god of war
Mars is the fourth planet from the sun and the second smallest planet in the solar system after Mercury Named after the Roman god of war it is often described as the ldquoRed Planet because the iron oxide prevalent on its surface gives it a reddish appearance
4
bull Mars is the fourth planet from the sunbull Mars is the seventh largest planet in our solar systembull Mars is referred to as the Red Planet due to its red soil made up of iron oxide
more commonly known as rustbull Mars is named after the Roman god of warbull The equatorial Diameter of Mars is 6805 kmbull The polar diameter of Mars is 6755 kmbull The Diameter of Mars is 6794 kmbull Martian day = 24 hours 34 minutes and 22 secondsbull Martian year = 687 Earth daysbull The mass of Mars is 641850000000000000000000 kgbull Surface temperature on Mars can range from the maximum of 310 K to a
minimum of 150 Kbull Atmospheric components on Mars consists of 9532 carbon dioxide 27
nitrogen 16 argon 013 oxygenbull Average Surface Temperature218K (-53ordm C)bull Average Distance from Sun2279 x 108 kmbull Average Density3934 kgm3
5
bull Moons of Mars = 21 Phobos ndash Diameter 22 km orbit 5981 km from the surface of Mars2 Deimos - Diameter 12 km orbit 20062 km form the surface of Mars
bull Mars atmospheric pressure at surface = 635 mbar gt 100th Earthrsquos atmospheric pressure
6
EarthMars Comparison
Distance from Sun 2279 x 108 km 1496 Million kmDiameter 6794 km 12742 kmLength of Year 687 Earth Days 36525 Days
Length of Day 24 hours 34 minutes and 22 sec
23 hours 56 minutes and 41 sec
Gravity 0375 that of Earth 266 times that of Mars
Temperature 218K (-53ordm C) 14degC
Temperature Range -127 ordm C to 17ordm C -88 ordm C to 58 ordm C Number of Moons 2 1
Mars Earth
7
8
Why this Journey
In an interview with The Hindu Radhakrishnan to a question on whatrsquos the most interesting on Mars he replies saying Life So we talk about Methanewhich is of biological origin or geological origin So we have a methane sensor plus a thermal infrared spectrometer These two together should be able to give some information He went on to say that ldquoWe want to look at environment of Mars for various elements like Deuterium-Hydrogen ratio We also want to look at other constituents mdash neutral constituent
After the EarthIts soil contains water to extractIt isnrsquot too cold or too hot There is enough sunlight to use solar panels Gravity 13 or 38 our Earths be sufficient for the human body to adapt Human speculationThe daynight a Mars day is 24 hours 39 minutes and 35 seconds 687 Days yearPlanet similar to earthextraterrestrial lifescientists to expect life on Mars
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
3
Mars Introduction
Mars is the fourth planet from the Sun and is commonly referred to as the Red Planet The rocks soil and sky have a red or pink hue The distinct red color was observed by stargazers throughout history It was given its name by the Romans in honor of their god of war
Mars is the fourth planet from the sun and the second smallest planet in the solar system after Mercury Named after the Roman god of war it is often described as the ldquoRed Planet because the iron oxide prevalent on its surface gives it a reddish appearance
4
bull Mars is the fourth planet from the sunbull Mars is the seventh largest planet in our solar systembull Mars is referred to as the Red Planet due to its red soil made up of iron oxide
more commonly known as rustbull Mars is named after the Roman god of warbull The equatorial Diameter of Mars is 6805 kmbull The polar diameter of Mars is 6755 kmbull The Diameter of Mars is 6794 kmbull Martian day = 24 hours 34 minutes and 22 secondsbull Martian year = 687 Earth daysbull The mass of Mars is 641850000000000000000000 kgbull Surface temperature on Mars can range from the maximum of 310 K to a
minimum of 150 Kbull Atmospheric components on Mars consists of 9532 carbon dioxide 27
nitrogen 16 argon 013 oxygenbull Average Surface Temperature218K (-53ordm C)bull Average Distance from Sun2279 x 108 kmbull Average Density3934 kgm3
5
bull Moons of Mars = 21 Phobos ndash Diameter 22 km orbit 5981 km from the surface of Mars2 Deimos - Diameter 12 km orbit 20062 km form the surface of Mars
bull Mars atmospheric pressure at surface = 635 mbar gt 100th Earthrsquos atmospheric pressure
6
EarthMars Comparison
Distance from Sun 2279 x 108 km 1496 Million kmDiameter 6794 km 12742 kmLength of Year 687 Earth Days 36525 Days
Length of Day 24 hours 34 minutes and 22 sec
23 hours 56 minutes and 41 sec
Gravity 0375 that of Earth 266 times that of Mars
Temperature 218K (-53ordm C) 14degC
Temperature Range -127 ordm C to 17ordm C -88 ordm C to 58 ordm C Number of Moons 2 1
Mars Earth
7
8
Why this Journey
In an interview with The Hindu Radhakrishnan to a question on whatrsquos the most interesting on Mars he replies saying Life So we talk about Methanewhich is of biological origin or geological origin So we have a methane sensor plus a thermal infrared spectrometer These two together should be able to give some information He went on to say that ldquoWe want to look at environment of Mars for various elements like Deuterium-Hydrogen ratio We also want to look at other constituents mdash neutral constituent
After the EarthIts soil contains water to extractIt isnrsquot too cold or too hot There is enough sunlight to use solar panels Gravity 13 or 38 our Earths be sufficient for the human body to adapt Human speculationThe daynight a Mars day is 24 hours 39 minutes and 35 seconds 687 Days yearPlanet similar to earthextraterrestrial lifescientists to expect life on Mars
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
4
bull Mars is the fourth planet from the sunbull Mars is the seventh largest planet in our solar systembull Mars is referred to as the Red Planet due to its red soil made up of iron oxide
more commonly known as rustbull Mars is named after the Roman god of warbull The equatorial Diameter of Mars is 6805 kmbull The polar diameter of Mars is 6755 kmbull The Diameter of Mars is 6794 kmbull Martian day = 24 hours 34 minutes and 22 secondsbull Martian year = 687 Earth daysbull The mass of Mars is 641850000000000000000000 kgbull Surface temperature on Mars can range from the maximum of 310 K to a
minimum of 150 Kbull Atmospheric components on Mars consists of 9532 carbon dioxide 27
nitrogen 16 argon 013 oxygenbull Average Surface Temperature218K (-53ordm C)bull Average Distance from Sun2279 x 108 kmbull Average Density3934 kgm3
5
bull Moons of Mars = 21 Phobos ndash Diameter 22 km orbit 5981 km from the surface of Mars2 Deimos - Diameter 12 km orbit 20062 km form the surface of Mars
bull Mars atmospheric pressure at surface = 635 mbar gt 100th Earthrsquos atmospheric pressure
6
EarthMars Comparison
Distance from Sun 2279 x 108 km 1496 Million kmDiameter 6794 km 12742 kmLength of Year 687 Earth Days 36525 Days
Length of Day 24 hours 34 minutes and 22 sec
23 hours 56 minutes and 41 sec
Gravity 0375 that of Earth 266 times that of Mars
Temperature 218K (-53ordm C) 14degC
Temperature Range -127 ordm C to 17ordm C -88 ordm C to 58 ordm C Number of Moons 2 1
Mars Earth
7
8
Why this Journey
In an interview with The Hindu Radhakrishnan to a question on whatrsquos the most interesting on Mars he replies saying Life So we talk about Methanewhich is of biological origin or geological origin So we have a methane sensor plus a thermal infrared spectrometer These two together should be able to give some information He went on to say that ldquoWe want to look at environment of Mars for various elements like Deuterium-Hydrogen ratio We also want to look at other constituents mdash neutral constituent
After the EarthIts soil contains water to extractIt isnrsquot too cold or too hot There is enough sunlight to use solar panels Gravity 13 or 38 our Earths be sufficient for the human body to adapt Human speculationThe daynight a Mars day is 24 hours 39 minutes and 35 seconds 687 Days yearPlanet similar to earthextraterrestrial lifescientists to expect life on Mars
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
5
bull Moons of Mars = 21 Phobos ndash Diameter 22 km orbit 5981 km from the surface of Mars2 Deimos - Diameter 12 km orbit 20062 km form the surface of Mars
bull Mars atmospheric pressure at surface = 635 mbar gt 100th Earthrsquos atmospheric pressure
6
EarthMars Comparison
Distance from Sun 2279 x 108 km 1496 Million kmDiameter 6794 km 12742 kmLength of Year 687 Earth Days 36525 Days
Length of Day 24 hours 34 minutes and 22 sec
23 hours 56 minutes and 41 sec
Gravity 0375 that of Earth 266 times that of Mars
Temperature 218K (-53ordm C) 14degC
Temperature Range -127 ordm C to 17ordm C -88 ordm C to 58 ordm C Number of Moons 2 1
Mars Earth
7
8
Why this Journey
In an interview with The Hindu Radhakrishnan to a question on whatrsquos the most interesting on Mars he replies saying Life So we talk about Methanewhich is of biological origin or geological origin So we have a methane sensor plus a thermal infrared spectrometer These two together should be able to give some information He went on to say that ldquoWe want to look at environment of Mars for various elements like Deuterium-Hydrogen ratio We also want to look at other constituents mdash neutral constituent
After the EarthIts soil contains water to extractIt isnrsquot too cold or too hot There is enough sunlight to use solar panels Gravity 13 or 38 our Earths be sufficient for the human body to adapt Human speculationThe daynight a Mars day is 24 hours 39 minutes and 35 seconds 687 Days yearPlanet similar to earthextraterrestrial lifescientists to expect life on Mars
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
6
EarthMars Comparison
Distance from Sun 2279 x 108 km 1496 Million kmDiameter 6794 km 12742 kmLength of Year 687 Earth Days 36525 Days
Length of Day 24 hours 34 minutes and 22 sec
23 hours 56 minutes and 41 sec
Gravity 0375 that of Earth 266 times that of Mars
Temperature 218K (-53ordm C) 14degC
Temperature Range -127 ordm C to 17ordm C -88 ordm C to 58 ordm C Number of Moons 2 1
Mars Earth
7
8
Why this Journey
In an interview with The Hindu Radhakrishnan to a question on whatrsquos the most interesting on Mars he replies saying Life So we talk about Methanewhich is of biological origin or geological origin So we have a methane sensor plus a thermal infrared spectrometer These two together should be able to give some information He went on to say that ldquoWe want to look at environment of Mars for various elements like Deuterium-Hydrogen ratio We also want to look at other constituents mdash neutral constituent
After the EarthIts soil contains water to extractIt isnrsquot too cold or too hot There is enough sunlight to use solar panels Gravity 13 or 38 our Earths be sufficient for the human body to adapt Human speculationThe daynight a Mars day is 24 hours 39 minutes and 35 seconds 687 Days yearPlanet similar to earthextraterrestrial lifescientists to expect life on Mars
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
7
8
Why this Journey
In an interview with The Hindu Radhakrishnan to a question on whatrsquos the most interesting on Mars he replies saying Life So we talk about Methanewhich is of biological origin or geological origin So we have a methane sensor plus a thermal infrared spectrometer These two together should be able to give some information He went on to say that ldquoWe want to look at environment of Mars for various elements like Deuterium-Hydrogen ratio We also want to look at other constituents mdash neutral constituent
After the EarthIts soil contains water to extractIt isnrsquot too cold or too hot There is enough sunlight to use solar panels Gravity 13 or 38 our Earths be sufficient for the human body to adapt Human speculationThe daynight a Mars day is 24 hours 39 minutes and 35 seconds 687 Days yearPlanet similar to earthextraterrestrial lifescientists to expect life on Mars
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
8
Why this Journey
In an interview with The Hindu Radhakrishnan to a question on whatrsquos the most interesting on Mars he replies saying Life So we talk about Methanewhich is of biological origin or geological origin So we have a methane sensor plus a thermal infrared spectrometer These two together should be able to give some information He went on to say that ldquoWe want to look at environment of Mars for various elements like Deuterium-Hydrogen ratio We also want to look at other constituents mdash neutral constituent
After the EarthIts soil contains water to extractIt isnrsquot too cold or too hot There is enough sunlight to use solar panels Gravity 13 or 38 our Earths be sufficient for the human body to adapt Human speculationThe daynight a Mars day is 24 hours 39 minutes and 35 seconds 687 Days yearPlanet similar to earthextraterrestrial lifescientists to expect life on Mars
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
9
The Launch Vehicle - PSLV-C25 will inject the Spacecraft into an Elliptical Parking Orbit with a perigee of 250 km and an apogee of 23500 km With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceWhen spacecraft reaches nearest pointof Mars (Peri-apsis) it is maneuvered in to an elliptical orbit around Mars by firing the Liquid Engine The spacecraft then moves around the Mars in an orbitwith Peri-apsis of 366 km and Apo-apsisof about 80000 km
Mission Plan
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
10
MISSION OBJECTIVES ISRO website stated that one of the main objectives of the first Indian mission to Mars is to develop the technologies required for design planning management and operations of an interplanetary mission A Technological Objectives 1 Design and realisation of a Mars orbiter with a capability to survive and perform Earth bound
manoeuvres cruise phase of 300 days Mars orbit insertion capture and on-orbit phase around Mars
2 Deep space communication navigation mission planning and management and incorporate autonomous features to handle contingency situations
B Scientific Objectives 3 Exploration of Mars surface features 4 morphology5 mineralogy 6 and Martian atmosphere by indigenous scientific instruments7 Existence of life
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
11
LAUNCH -PSLV C25 XL
bull The Polar Satellite Launch Vehicle (PSLV) is an expendable launch system developed and operated by the Indian Space Research Organization (ISRO) It was developed to allow India to launch its Indian Remote Sensing (IRS) satellites into sun synchronous orbits
bull PSLV include Indias first lunar probe Chandrayaan-1 Indias first interplanetary mission Mangalyaan (Mars orbiter) and Indias first space observatory Astrosat
bull PSLV-XL is the upgrated version of Polar Satellite Launch Vehicle in its standard configuration boosted by more powerful stretched strap-on boosters
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
Mangalyan ( Mars Orbiter Mission)
Specifications
Date Of Announcement 15 August 2012 Date Of Launch 5 November 2013 Place Of Launch SDSC (Sriharikota) Type Of Rocket Used PSLV XL-C25 Type Of A Mission Mars Orbiter Mission Capability (i) 4 stage vehicle
(ii) Multi orbital Capability Spacecraft Weight At Lift Off 1337 Kg Propellant Loaded 852 Kg Scientific Payload Weight 15 Kg Overall height 44 m Diameter 28 m Type Of Fuel Used SolidLiquidCryo
Propellant Mission Cost 450 Cr INR
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
13
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
14
MassThe lift-off mass was 1350 kg including 852 kg of propellant massDimensionsCuboid in shape of approximately 15 m PowerElectric power is generated by three solar array panels of 18 times 14 m each Electricity is stored in a 36 Ah Li-ion batteryPropulsionLiquid fuel engine of 440 N thrust is used for orbit raising and insertion in Martian orbit and 8 numbers of 22 N thrusters are used for attitude control CommunicationsTwo 230 W TWTAs and two coherent transponders The antenna array consists of a low-gain antenna a medium-gain antenna and a high-gain antenna
SPACECRAFT
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
15
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
16
PAYLOADS
Atmospheric studiesbull Lyman-Alpha Photometer (LAP)bull Methane Sensor For Mars (MSM)
Particle environment studies Mars Exospheric Neutral
Composition Analyser (MENCA)Surface imaging studies
bull Thermal Infrared Imaging Spectrometer (TIS)
bull Mars Color Camera (MCC)
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
17
LAP Lyman-Alpha Photometer 197 kgMSM Methane Sensor For Mars 294 kgMENCA Mars Exospheric Neutral Composition Analyser 356 kgTIS Thermal Infrared Imaging Spectrometer 320 kgMCC Mars Colour Camera 127 kg
Payload
Scientific instrumentsThe 15 kg (33 lb) scientific payload consists of five instruments
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
18
LYMAN ALPHA PHOTOMETER (LAP)
Lyman Alpha Photometer (LAP) is an absorption cell photometer It measures the relative abundance of deuterium and hydrogen from lyman-alpha emission in the Martian upper atmosphere (typically Exosphere and exobase) Measurement of DH (Deuterium to Hydrogen abundance Ratio) allows us to understand especially the loss process of water from the planet
The objectives of this instrument are as followsEstimation of DH ratioEstimation of escape flux of H2 coronaGeneration of Hydrogen and Deuterium coronal profiles
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
19
Methane Sensor for Mars (MSM)
MSM is designed to measure Methane (CH4) in the Martian atmosphere with PPB accuracy and map its sources Data is acquired only over illuminated scene as the sensor measures reflected solar radiation Methane concentration in the Martian atmosphere undergoes spatial and temporal variations
Specific areas of interest1Algorithm development for Methane detection in atmosphere of Mars2Mars reflectance changes due to dynamic atmosphere using MSM3Radio ative transfer modeling in VNIR (visible and near-infrared) part of EM spectrum
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
20
Mars Exospheric Neutral Composition Analyser (MENCA)
MENCA is a quadruple mass spectrometer capable of analyzing the neutral composition in the range of 1 to 300 amu(atomic mass unit) with unit mass resolution
Specific areas of interest 1Exopsheric composition of Mars2Atmospheric escape from Mars
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
21
Thermal Infrared Imaging Spectrometer (TIS)
TIS measure the thermal emission and can be operated during both day and night Temperature and emissivity are the two basic physical parameters estimated from thermal emission measurement Many minerals and soil types have characteristic spectra in TIR region TIS can map surface composition and mineralogy of Mars
Specific areas of interest1Algorithm development for analysis of TIS data2Inversion of surface temperature of Mars using TIS data
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
22
Specific areas of interest1Geomorphology and morphometric analysis of martian volcanoes2Geomorphology and morphometric analysis of fluvial landforms3Aeolian processes on Mars4Dust storms5Dust devils6Wind streaks7Study of geomorphology of Mars with terrestrial analogues
Mars Color Camera (MCC)This tri-color Mars color camera gives images amp information about the surface features and composition of Martian surface They are useful to monitor the dynamic events and weather of Mars MCC will also be used for probing the two satellites of Mars-Phobos amp Deimos It also provides the context information for other science payloads
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
23
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
24
Mission Phases or TrajectoryMars is to develop the technologies required for design planning management and operations of an interplanetary mission
A Geocentric Phases The spacecraft is injected into Elliptical parking orbit by the launcher ISRO uses a method of travel called Hohmann Transfer Orbit or Minimum Energy
Transfer Orbit to send spacecraft from Earth to Mars Six main engines burns in this phase for six mid night maneuvers At the end of this phase the spacecraft is escaped from Earth Sphere Of Influence(SOI)
Earth SOI is 918347
B Heliocentric Phases Spacecraft enters into Mars tangential orbit This Phase depends on relative position of Earth Mars and Sun Such relative arrangement recur periodically at interval of about 780 days
C Martian Phases The spacecraft is arrives at the Mars Sphere Of Influence(SOI)[573473 KM from surface
of Mars] At the time of spacecraft reaches the closest approach to Mars It is captured into planed
orbit around Mars
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
25
Earth Parking OrbitIt would be extremely challenging to schedule launches so that they happened at precisely the right time to launch a spacecraft directly from the pad into a trajectory to an external body like the ISS the Moon or Mars It might even be impossible for particular launch locations to do thatSo instead a spacecraft is launched into a stable orbit and the spacecraft then goes around the Earth in that orbit until the timing and geometry are right to fire its engine again initiating a trajectory to its target That temporary orbit is called a parking orbit
Perform checks of the following systems1048766 Biomedical amp safety equipment1048766 Environmental control system1048766 Comm amp instrumentation system1048766 Electrical power system (EPS)1048766 Stabilization and control system (SCS)1048766 Crew equipment system1048766 SM propulsion system (SPS)1048766 SM reaction control system (RCS)1048766 Command Module Computer optics1048766 Entry monitoring system (EMS)
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
26
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
27
In order to achieve the velocity required to escape the earthrsquos gravity(escape velocity) 6 orbit raising manoeuvers were performed on 6th 7th 8th 10th 11th and 15th November
PSLV rocket took the spacecraft in the Near Earth Orbit also known as LEO ( Lower Earth Orbit ) Very first orbits in which the spacecraft entered and then raised to higher ones are called EPOs ( Earth
Parking Orbits ) LEO Perigee 240 Km LEO Apogee 24000 Km Orbit increment was done when the satellite was at the perigee point It has undergone through Orbit Raising Maneuver 5 times Final Apogee 193000 Km Corresponding Speed Of Satellite ~ 11 Kmsec
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
28
With six Liquid Engine firing the spacecraft is gradually maneuvered into a hyperbolic trajectory with which it escapes from the Earthrsquos Sphere of Influence (SOI) and arrives at the Mars Sphere of InfluenceThe spacecraft then embarked on its 10-month 670 million kms long journey towards Mars
On 30th November 2013 the engines
of MOM were fired for 23
minutesThe earthrsquos escape
velocity was achieved by MOM and the spacecraft
left the earthrsquos orbit
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
29
The orbit of MOM around Mars is highly elliptical with periapsis ~370 km and apoapsis ~80000 km inclination 151 degree and orbital period 315 sols The spacecraft mass is 1350 kg with dry mass of 500 kg and science payload mass of 14 kg
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
30
bull launch will place from sriharikota and the Mars Orbiter will be placed into Earth orbit then six engine firings will raise that orbit to one with an apogee of 215000 km and a perigee of 600 km where it will remain for about 25 days
bull A final firing in 30 November 2013 will send MOM onto an interplanetary trajectory
bull Mars orbit insertion is planned for 21 September 2014 and would allow the spacecraft to enter a highly elliptical orbit of 422 km x 77000 km around Mars
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
31
The government of India approved the project on 3 august 2012 after the Indian Space Research Organization completed 125 crore of required studies for the orbiter The total project cost may be up to 454 crore The satellite costs 153 crore and the rest of the budget has been attributed to ground stations and relay upgrades that will be used for other ISRO projects
MISSION COST
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
32
TRACKING AND COMMAND-INDIAN DEEP SPACE NETWORK (IDSN)-INTERNATIONAL GROUND STATIONS
The Indian Space Research Organisation Telemetry Tracking and Command Network(ISTTCN) performed navigation and tracking operations for the launch with ground stations at Sriharikota Port Blair Brunei and Biak in Indonesia and after the spacecrafts apogee becomes more than 100000 km two large 18-metre and 32-metre diameter antennas of the Indian Deep Space Network will be utilised NASAs Deep Space Network will provide position data through its three stations located in Canberra Madrid and Goldstone on the US West Coast during the non-visible period of ISROs networkThe South African National Space Agencys (SANSA) Harte beesthoek (HBK) ground station is also providing satellite tracking telemetry and command services Additional monitoring is provided by technicians on board two leased ships from the Shipping Corporation of India SCI Nalanda and SCI Yamuna which are currently in position in the South Pacific
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
33
bull The radio waves (to be more precise in the case microwaves) travelling at the speed of light(300000kms) take 10minutes to travel from Earth to a spacecraft orbiting Mars
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
34
Phobos one of the two natural satellites of Mars silhouetted against the Martian surface
Taken using the Mars Colour Camera from an altitude of 8449 km
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
35
Regional dust storm activities over Northern Hemisphere of Mars -captured by MCC
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
36
1 K Radhakrishan ndash Chairman ISRO2 M Annadurai ndash Programme Director MOM3 S Ramakrishnan - Director of Vikram Sarabhai Space Centre4 S K Shivkumar ndash Orbiting payload Director ISAC5 V Adimurthy - Mission Concept Designer of Mars Orbiter Mission 6 P Kunhikrishnan ndash Launch Mission Director PSLV-XL7 Chandradathan - Director of the Propulsion Systems 8 AS Kiran Kumar ndash Director SAC9 MYS Prasad ndash Director SDSC and chairman Launch Authorisation
Board10 S Arunan ndash Project Director MOM11 B Jayakumar ndash Launch Vehicle Director PSLV12 MS Pannirselvam - The chief general manager of range operation
director 13 V Kesavaraju ndash Post-Launch Mission Director MOM14 B S Chandrashekar ndash Director ISTRAC15 P Robert ndash Operations Director MOM
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
37
K RadhakrishanChairman ISRO
M AnnaduraiProgr Director MOM
S RamakrishnanDirectorVSSC
S K ShivkumarOrbiting payload Director
ISAC
V AdimurthyMission Concept Designer(MOM)
P KunhikrishnanLaunch Mission Director
PSLV-XL
Madhavan ChandradathanDirector Propulsion Systems
VSSC
AS Kiran KumarDirector SAC
S Arunan Project Director
MOM
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
38
CONCLUSION
The success of Mangalyaan showed world nations Indian and ISRO superiority in the space technology
The primary objective of the Mars Orbiter Mission is to showcase Indias rocket launch systems spacecraft-building and operations capabilities
THANK YOUhellip
- Slide 1
- Slide 2
- Slide 3
- Slide 4
- Slide 5
- Slide 6
- Slide 7
- Slide 8
- Slide 9
- Slide 10
- Slide 11
- Slide 12
- Slide 13
- Slide 14
- Slide 15
- Slide 16
- Slide 17
- Slide 18
- Slide 19
- Slide 20
- Slide 21
- Slide 22
- Slide 23
- Slide 24
- Slide 25
- Slide 26
- Slide 27
- Slide 28
- Slide 29
- Slide 30
- MISSION COST
- Slide 32
- Slide 33
- Slide 34
- Slide 35
- Slide 36
- Slide 37
- CONCLUSION
-
