Chandrayaan-1 Mission

Colloquium at TIFR, Mumbai

August 17, 2007

K Thyagarajan

Prog. Dir, IRS/SSS

ISRO Satellite Centre

When the media asked former chairman, ISRO

whether India can afford to send a craft to the

Moon, he replied

“Can India afford not to go the Moon”

Outline of presentation

Why go to the Moon?

What’s known about Moon?

Chandrayaan-1 Mission objectives

Payloads in the Mission

Spacecraft configuration

Launch vehicle

Mission profile

Imaging strategy for lunar coverage

Deep Space Network (DSN)

Indian Space science data Center (ISSDC)

Why go to the Moon

The origin of Moon is still not clearly understood and there have

been several speculations

Space programme for Lunar exploration was undertaken as early as

1959.

Several Lunar exploratory missions since then have been conducted

Interest in Lunar science was renewed when imaging systems

onboard NASA’s “Galileo” spacecraft sent picture of the previously

unexplored regions of the Moon during 1990

Galileo identified a large impact basin, about 2500km in diameter

and 10 to 12 km deep in the south pole Aitken Region on the far

side of the Moon

Why go to the Moon (Contd ..)

With the development of new technology, a new era of lunar

exploration by many countries have now begun using advanced

instruments and microelectronics

Apart from scientific interest, the Moon could have economic

benefits to mankind and could be of strategic importance

The Moon’s surface has about one million tonnes of Helium-3

Moon contains 10 times more energy in Helium-3 than all the fossil fuels

on Earth

Helium-3 is believed to be fuel of the future

Outpost for further planetary explorations and possible human

settlements

What is known about Moon?

Landing and Sample Return Missions

Apollo 11-17 (13),

Luna 16, 20, 24 (1969-74)

Orbiting Missions

Clementine (1994)

UVVIS, NIR, LWIR, LIDAR

Mineral Mapping

Lunar Prospector (1998)

-ray, , Neutron Spectrometers,

Magnetometer, Electron

Reflectometer, Doppler Gravity

Chemical Mapping, Water (?)

SMART-1(2003)

Mapping of geological and

mineralogical resources (Res: 40m)

A-13

A-12

A-14

A-15

A-16

A-11

A-17

L-24

L20

L-16

Future Lunar missions

Chang’e-1 by China scheduled for late 2007

3D map of Moon, Moon’s Soil composition & mineral distribution

Selene by Japan scheduled for late 2007

Moon’s Topography, mineral content and gravity

LRO by USA scheduled in late 2008

Water-ice at poles, selection of soft-landing sites, etc

Russian Mission Scheduled for 2009

Understanding the origin and Evolution of the Moon

Water on Moon?

Physical Properties of the Moon

Topography

Gravity

Magnetic Field

Radiation Environment

Special Regions of Interest:

Polar Regions ,

South Pole Aitken Region,

Selected Basins and Craters with central uplift

The Lunar Far-side: Rock types, Chemistry

Nature of the Lunar Crust

The bulk chemistry of Moon

Objectives of the Chandrayaan-1 Mission

Simultaneous Mineralogical, Chemical & Photo-geological Mapping

at resolutions better than previous and currently planned Lunar

missions

High resolution VIS-NIR mapping of the lunar surface to identify

Fe, Al, Mg, Ti bearing mineral with high spatial resolution (100m)

3D mapping of lunar surface at very high spatial resolution (~5 m)

High Resolution Laser ranging for topographical Map of the Moon

(~0.1 deg longitudinal separation grids)

Create Expertise & Motivate the Young Minds in Space and

Planetary Science

Configuration : 100 km polar orbiter

Observation Period : 2 years

Chandrayaan-1 Mission

Hyper Spectral Imager (HySI) (0.4-0.9µm)

Terrain Mapping Camera (TMC)(0.5-0.75 µm)

Lunar Laser Ranging Instrument (LLRI)

Low energy X-ray spectrometer (LEX) (1-10KeV)

High energy X- ray spectrometer (HEX) (10-200KeV)

A new era of International Cooperation

Based on science objectives and spacecraft resources, several AO

proposals were accepted; they will complement/add to the Indian

experiments to meet the basic science goals of the mission.

I. IR spectrometers for mineral mapping (SIR-2 and MMM)

II. An experiment to detect neutral atoms (SARA)

III. An experiment to search for water-ice at the poles (mini-SAR)

IV. An experiment to monitor energetic particle environment (RADOM)

Sun movement restricted to 1.50 w.r.t lunar equator

Eternal lights at polar high land regions

Low temperature excursions (-150 C to –500 C)

Presence of water nearby likely

Continuous solar power generation possible

Lunar environment - Thermal

South Pole Atkin Region (SPAR), largest impact basin

in Solar System extends from South pole to 400 S

latitude on the far side

No known Seismic activity, no surface winds

Hard shadows, no atmospheric dispersion

Crystalline lunar soil can be paved glassy using

microwaves, roads, craters to parabolic antenna

backplanes

Lunar environment - Other

Comparison of Moon’s & Earth’s Orbit

Moon Earth

Semi-major axis 384.4 x 103 km 1.000 AU

Revolution period 27.32 days 365.26 days

Orbit inclination18.3° to 29° w.r.t

Earth’s equator0.00 w.r.t ecliptic plane

Eccentricity 0.055 0.017

Obliquity 6.7° 23.4°

Rotation period 27.32 days 23 h 56 min

Radius 1738 km 6378 km

Mass 7.35 x 1022 kg 5.98 x 1024 kg

Mean density 3340 kg/m3 5520 kg/m3

Escape velocity at

surface2.38 km/s 11.2 km/s

The moon is a satellite of earth in a slightly elliptical orbit, inclination

w.r.t the earth equator oscillating between 28035’ and 18021’ with a

period of 18.6 years.

The angle between lunar equator and ecliptic plane is approximately

1.50 resulting in poor illumination of polar regions

No Atmospheric Drag

No SELENO-Magnetic Fields

100 Km Circular Polar Orbit (Period of 118 min.) selected to meet

the Imaging requirements

Main Characteristics of Moon’s Orbit

CHANDRAYAAN-1 ORBIT

• Altitude: 100km

• Inclination: 90°

• Period: 117.6 min

• Mean ground velocity: 1.54 km/s

• Earth as seen by Moon: 1.9° - 2.1°

• Beam width of 0.7 m X-band antenna: 3.6°

• Moon disc at satellite: ±70°

SL.NO

.

PAYLOAD Spectral band Sensor Config Objective

1 TMC 0.5 to 0.85μm Three Stero

Cameras

Topography

2 HySI-VINR 0.4 to 0.92μm Wedge filter Mineral mapping

3 LLRI 1064nm, 10mJ Topography &Gravity

4 HEX 20 – 250 keV CdZnTe Detector Chemical mapping

5 IMPACTOR -------------- Technology Demo

6 CIXS (LEX) 0.5 to 10keV Swept Charge

CCDChemical mapping

7 Mini-SAR 2.5GHz Detection of poalr ice

8 SIR-2 0.93 to 2. Mineral Mapping

9 SARA 10eV to 2keV Mass

spectrometer

Atmospheric

neutrals& magnetic

anomaly

10 RADOM >8Kev Si Semiconductor Radiation monitor

11 MMM 0.4-3.0μm Mineral Mapping

Payloads Payloads from ISRO

Terrain Mapping Camera with front, nadir and aft views(TMC).

Hyper Spectral Imager(HySI).

Lunar Laser Ranging Instrument (LLRI).

High Energy X-ray payload(HEX).

Moon Impact Probe (MIP)

Payloads from international agencies

Low Energy X-ray (LEX)payload (CIXS). From Rutherford Appleton

Laboratory (RAL),UK / ESA

Mini SAR from Applied Physics Laboratory (APL), USA under an MOU

with NASA

SIR-2 from Max Plank Institute, Germany under an MOU with ESA

Radiation Dose Monitor from Bulgarian Academy of Sciences

Sub-keV Atom Reflecting Analyser (SARA) Experiment developed jointly

by IRF Sweden, SPL-VSCC India, ISAS/JAXA Japan and VBE

Switzerland under an MOU with ESA

Moon Mineralogy Mapper (M3) from JPL, US., under an MOU with NASA

Terrain Mapping Camera (TMC)

Stereoscopic imaging instrument in panchromatic

spectral band for generating high resolution three

dimensional map of Moon

Consists of fore, nadir and aft detectors housed in single

enclosure

Spatial: Swath – 20km, Resolution – 5m

Spectral: 0.5 to 0.85µm

4000 pixel, 7µ linear APS detector

Hyper Spectral Imager (HySI)

In visible and near infra-red band

Spatial: Swath – 20km, Resolution – 80m

Spectral: 0.4 to 0.95µm, resolution better than

15nm

256 x 512 pixel, 50µ area APS detector

Lunar Laser Ranging Instrument (LLRI)

Objectives

To determine the global topographical field of Moon using the laseraltimetry data

To determine an improved model of the lunar gravity field

To supplement TMC and HySI payloads

Laser wavelength: 1064 nm

Laser energy: 10 mj

Vertical Resoultion: < 5m

Detector: Avalanche Photodiode

First time coverage of polar regions of Moon

High Energy X-ray Spectrometer (HEX)

Objectives

Identify degassing fault zones by mapping of 222Rn and its radioactive daughter210Pb, helps understanding volatile transport on Moon

To determine the surface composition of Pb-210 in the uranium decay series byit’s 46.5 keV gamma ray

To determine the integral flux of gamma rays coming out of Moon in the region10 – 250 keV

Energy Resolution: <7% @ 60 keV

Energy range: 20 – 250 keV

Spatial resolution: 20 km

Swath: 40 km x 40 km

Detector: CdZnTe (CZT)

Moon Impact Probe (MIP)

Objectives

Scientific exploration of the Moon near range

To design, develop and demonstrate technologies required forimpacting a probe at the desired location on the Moon

Qualify some of the techniques required for soft-landing missions

Payloads

Mass spectrometer to assess the lunar atmosphere

Radar altimeter to measure the altitude with a resolution of 5m

Video imaging system (VIS) to take photographs of Moon’s surface

From 100km orbit, it takes ~18 minutes to hit the Moon surface

Low Energy X-ray Spectrometer (LEX)

Updated version of Smart-1 payload

Consists of two instruments

Chandrayaan-1 Compact Imaging X-ray Spectrometer (C1XS)

Main instrument

X-ray Solar Monitor (XSM)

Provides incident solar flux as input to C1X

Objective: To carry-out high quality X-ray spectroscopic mapping of theMoon in order to study elemental abundance of Moon

Basically measures fluorescent emissions from the surface of Moon and alsomonitors incident Solar X-ray emissions

Detects Mg, Al, Fe and Si during non-Solar flare conditions (C1X)

Detects Ca, Ti during Solar flare conditions (XSM)

Energy range: 0.5 to 10 keV

Miniature Synthetic Aperture Radar(Mini-SAR)

Objective

To map polar regions at an incident angle of app. 37 deg.Basically looks for ice / water deposits

To resolve discrepancy in the data available from Clementine,Lunar Prospector and Arecibo Radar satellites with respect tonature and amount of deposits in the lunar polar region

Range swath: 44km, Azimuth swath: 8km

Ground range resolution: 140m for altimeter

Radar system can operate as altimeter / scatterometer,radiometer and as a synthetic aperture radar

Smart Infra Red Spectrometer (SIR-2) Updated version of SMART-1 payload

It is a highly compact and near infra-red spectrometer

Objective

Analyze the lunar surface in various geological / mineralogical /topographical units

Study of vertical distribution of crystal material

Investigate the process of crater, maria and basin formation on Moon

Explore “Space Weathering” process of the lunar surface

Search for ices at the lunar poles

SIR-2 collects the Sun’s light reflected by the Moon

Spectral Wavelength: 0.93 to 24 µm

Spectral resolution: 6nm

Sub keV Atom Reflecting Analyzer (SARA)

Consists of two payloads

Chandrayaan Energetic Neutral Analyzer (CENA)

Solar Wind Monitor (SWIM)

Objective

Imaging of the surface magnetic anomalies (Moon doesn’t havemagnetic core, like in Earth. But Moon has different magneticfields at different surface areas which is an anomaly)

Studies of space weathering, i.e., physical and chemical changesthat occur to the exposed materials on the surface of the Moon

Imaging of Moon’s surface composition including imaging ofpermanently shadowed areas and search for volatile rich areas

Radiation Dose Monitor (RADOM)

Updated version of similar instrument flown in MIR spacestation since 1988

Objective

Measure the particle flux, deposited energy spectrum,accumulated absorbed dose rate in the lunar orbit and evaluatethe contribution of protons, neutron, electrons, gamma rays andenergetic galactic cosmic radiation nuclei

Provide an estimation of the dose map around Moon at differentaltitudes

To evaluate the shielding characteristics (if any exists) of theMoon near environment towards galactic and solar cosmicradiation and solar particle events

The experiment will be useful for future manned missions

Moon Mineralogy Mapper (M3)

Payload is solar reflected energy imaging spectrometer

Objective

To assess the mineral resources of the Moon

To characterize and map the composition of the surface at highspatial resolution

Spectral- Range: 0.7 – 3.0 µm, Resolution: 10nm

Radiometric: Range 0 to max. Lambertian, Sampling 12 bits

Spatial: Swath 40km, Resolution 30m

MiniSAR

HEXHySI

TMC

LLRI

SIR-2

MIP

RADOM

SWIM XSM

CENA

M3

CIXS

Spacecraft Configuration

S-band transmission through omni antenna

Configured with two 90 hemi-spherical coverage antennas with opposite polarisation placed on the diametrically opposite face in the S/C

X-band transmission through Steerable Dual Gimbal Antenna

Sensors – CASS, SPSS, Star sensor

BMU handles Command, Telemetry, AOCS functions

Bi propellant system for orbit raising & maintainence

CCSDS – compatible with world-wide network & DSN

Single bus / battery system Canted Solar panel generates 700 W on normal incidence

27 AH Li Ion battery

PLATFORM SPECIFICATIONS(NORMAL MODE POINTING AND STABILITY)

AxisAttitude

PointingRate

Yaw 0.05 3.0E-4 /s

Roll 0.05 3.0E-4 /s

Pitch 0.05 3.0E-4 /s

Post-facto attitude determination: 40 arc-sec for entire mission life

VIRTUAL CHANNEL - 0

1. TMC – APS1

2. TMC – APS2

3. TMC – APS3

4. HySI

VIRTUAL CHANNEL - 1

miniSAR

VIRTUAL CHANNEL - 3

1. MIP

2. C1XS

3. HEX

4. SIR-2

5. LLRI

6. SARA

7. RADOM

8. S-LBT

9. GYRO

10.STAR SENSOR

VIRTUAL

CHANNEL - 2

M3

SSR #1

SSR #2

SSR #3

Channel

coder

X-band

link

X-Band Downlinks from Chandrayaan-1

Mass Budget

Bus Elements (kg) 405.0

Payload (kg) 89.0

S/C Dry Mass (kg) 494.0

Growth Margin (kg) 9.0

Dry Mass (kg) 503.0

Propellant (kg) 797.5

Pressurant (kg) 3.5

Lift off Mass (kg) 1304.0

Power BudgetSub-system Sunlit (W) Eclipse (W)

HEX, LLRI, AO 44 44

IMAGING (Average) + CIXS 34(6+28) 0

DATA Tx 0 44

BUS 236 228

TOTAL 534 316

INT. LOSS (4%) 22 13

REQUIREMENT 556 329

GENERATION 607 27AH@ 25% DOD

MARGIN 51

DSN-18

Chandrayaan-1 Ground Segment

SpecificationsDSN-18 S/X

(ALL Phases)

DSN-32 S/X

(> 1 Lakh km)

Ant. Dia (m) 18.3 32

G/T (dB/K) 30.6 37.5

G/T looking at Moon (dB/K) 26.0 32.0

EIRP (dBW) 79 94/84

Antenna rates

Velocity (deg/s)

Accln. deg/s*2

10(Az) /1(El)

5/ 0.5

0.4

0.01

Tone Ranging Accuracy (m) 20 20

Range-rate

Accuracy (m/s)0.05 0.05

Surface finishing (wrt parabola) - 0.3mm rms

ISTRAC IDSN STATIONS – S BAND

Polar Satellite Launch Vehicle (PSLV)

Basic Capabilities

SSPO ( 725*725 km, i= 98.370 ) 1250 kg

LEO (300*300 km ) 3400 kg

GTO (240 * 36000 km, METSAT) 1050 kg

Chandrayaan-1 (260 X 24000 km) 1304 kg

Vehicle Configuration

(6S9+S139)+L40+S7+L2.5

Sun

Moon at Launch

ETOGTO

Lunar Transfer Trajectory

Lunar Insertion Manoeuvre

Mid Course Correction

Trans Lunar Injection

Initial Orbit ~ 1000 km

Final Orbit 100 km Polar

To achieve 100 x 100 km Lunar Polar Orbit.

PSLV to inject 1304 kg in GTO of 260 x 24000 km.

Lunar Orbital mass of 623 kg with 2 year life time.

Indian Lunar Mission

Launch Window

It is necessary to have a LOI manoeuvre when Moon is

at equator, i.e., when Moon is in the ascending or the

descending node.

Two launch opportunities in 28 days (lunar cycle) are

possible.

Capture at descending node is not favourable in all

seasons as Sun lies in the perigee side, causing long

shadows near apogee.

Maximum shadow allowed per orbit is 100 minutes

Transfer phase to lunar capture

SOI index 11032

0

50

100

150

200

250

300

350

400

0 50 100 150 200 250

Th

ou

sa

nd

s

Rad

ial

dis

tan

ce

fro

m E

art

h (

km

)

0

10

20

30

40

50

60

70

80

Th

ou

sa

nd

s

Rad

ial

dis

tan

ce

fro

m M

oo

n (

km

)

Time in hrs elapsed since injection (Launch Apr 09, 2008)

Injection parameters - version #1

Altitude = 511.063963km

Geodetic latitude -4.250270°

East Longitude 138.301821°

Velocity 9.707127°

Flight Path Angle 80.292873°

Velocity Azimuth 107.439542°

Orbit Size: 260km x 24075km

Inclination = 17.93742°

Arg Perigee = 169.06269°

CAP08AP09-NOM-00

Consolidated Network Stations

S.N Mission Phase Stations

1. Short Range Support (Perigee arc coverage) – S-band support

During Spacecraft separation Biak, Hawaii

During burn #1 (TM) TT, Kourou, Natal

During burn #2 & #3 (TM) Port Blair, Brunei, Biak

2. LEOP phase (upto 1 lakh km)

S-band support (TC, TM, TRK)Bangalore, Biak, MaryLand (APL),

Mauritius, Hawaii, Lucknow, Bearslake

X-band supportBangalore, Mauritius (post LEB #1),

Hawaii (post LEB #2 & #3)

3. DSN support

LEOP phaseBangalore, Bearslake, APL, JPL-

Goldstone

Normal phaseBangalore, Bearslake, APL,

JPL -Goldstone (on requirement)

Inertially fixed lunar polar orbit

Orbit regression is negligible.

Lunar sun synchronous orbit not possible.

Inertially fixed polar orbit experiences continuously varying sun

illumination over a year.

Lunar Orbit as seen from

Earth

Face on

T

Edge on

T+7 days

Face on

T+14 days

M M

Classification of Payloads

Illumination dependant TMC + HySI

M3

SIR-2

C1XS

Illumination independent LLRI

MiniSAR

SARA

HEX

Moon independent RADOM

XSM of C1XS

SWIM of SARA

Sun aspect variations in a year

M

4 Months

4 Months300

300

300

300

M

4 Months

4 Months300

300

300

300

Polar regionPrime zone

Imaging Strategy - Definitions

Prime Imaging season

Season in which the solar aspect angle at lunar equator is within ±45°. Seasoncomprises of 90 days centered around noon/midnight orbit suitable for opticalimaging.

Prime Imaging Zone

Region within ±60° latitude of lunar equator, sensitive to illumination variationresulting from sun movement over the season. This zone is covered by imagingpayloads within 60 days centered on noon/midnight orbit restricting the solaraspect angle within ±30° with respect to the lunar equator.

Polar zone

High latitude zones (beyond 60°) which are poorly illuminated and insensitive tosun movement. Low lands are permanently shadowed, high lands areperpetually under grazing sun rays. Imaging coverage is for 15 days wherein thesolar aspect angle is restricted in the bands of ±30° and ±45° respectively.

Imaging Strategy – Definitions …

Secondary Imaging season

Season in which the solar aspect angle at lunar equator is beyond±45°. Season comprises of 90 days centered on dawn/dusk orbit. Inthis period, payloads which are not dependent on groundillumination levels like mini-SAR, HEX, LEX, LLRI, SARA andRADOM are operated.

Imaging Cycle

All Sunlit longitudes of Moon are swept once in 28 days owing torotation about its own axis termed as an Imaging Cycle. Eachimaging season has TWO cycles.

DSN Visibility at 100 km orbit

Complete Lunar Surface Coverage

DSN support for payload data transmission Bangalore + APL-USA

Area covered in prime imaging zone 60º N to 60º S

Area covered in polar imaging zone90°N to 60°N,

90°S to 60°S

Latitude zone covered in one visible orbit 60°

No: of orbits visible / day 10

Time required to visit all longitudes 2 prime image seasons

Time available for each prime imaging season 3 months

Time available for each secondary imaging season 3 months

Number of prime imaging seasons 3

Number of secondary imaging seasons 2

Minimum time required to cover entire lunar surface 15 months

Distinct Mission Features

Features that affect payload data processing

Spacecraft yaw rotation

Imaging in ascending and descending paths

Varying Illumination conditions

Vernier ground track shifts

Variation in altitude

Features that affect downlink

Sun outage

Rain attenuation during Moon rise / Moon set

48 m M.S72 m

P.E.S48 m

M.S 37 m E.S

UMBRA

PENUMBRA

35 m

M.S

72 m

P.E.S

48 m

M.S

M

48 m

P.E.S

13 m

P.E.S

M.S – Moon shadow, P.E.S – Part Earth Shadow, E.S – Earth Shadow

Worst Case Eclipse – Earth & Moon Shadow

48 27.5 42.5 48

9.5

519.5

48 42.5 27.5 48

MS ES PESPESLITPES PES

LITMS MS MS

Duration in minutes

MS –Moon Shadow

LIT - Illumination period

PES – Partial Earth Shadow

ES – Earth Shadow

WORST CASE ECLIPSE–EARTH AND MOON SHADOW

Total Duration: 6.7 hours

SUMMARY OF LUNAR ECLIPSES

(2008-2010)

Date Eclipse

Type Saros

Umbral

Mag

Eclipse

Duration

(hh:mm)

Geographic Regions of Eclipse

Visibility

21 Feb, 2008 Total 133 1.111 03:36

00:51 C.Pacific, Americas, Europe, Africa

16 Aug, 2008 Partial 138 0.813 03:09 S.America, Europe, Africa, Asia, Aus

09 Feb, 2009 Penumbral 143 -0.083 - E Europe, Asia, Aus, Pacific, W

N.A

07 Jul, 2009 Penumbral 110 -0.909 - Aus, Pacific, Americas

06 Aug, 2009 Penumbral 148 -0.661 - Americas, Europe, Africa, W Asia

31 Dec, 2009 Partial 115 0.082 01:02 Europe, Africa, Asia, Aus

26 Jun, 2010 Partial 120 0.0542 02:44 E Asia, Aus, Pacific, W Americas

21 Dec, 2010 Total 125 1.262 03:29

01:13

E Asia, Aus, Pacific, Americas,

Europe

ISSDC Context

Payload Reception

Stations

Principal

Investigators

S/C control center

ISSDC

Payload

Operation Centers

Science

Working Group

Science

Data Users

Time Allocation

Committee

Space Science

Mission Projects

S/W Developers –

data products, tools

Payload

Developers

ISSDC functions

• Primary Functions

– Ingest / Archive / Data Management

– Data processing

– Search & Order / Access & Dissemination

– Interface to Spacecraft control centers, Data

reception centers, Payload designers, Principal

investigators, Mission software developers and

Science data users

ISSDC facilities• Server and Storage Support Area

• Network Support Area

• Public Network Access Workspace

• Private Network Access Workspace

• SATCOM Network Access Workspace

• Software & System Support Area

• System Administration Workspace

• System test and Maintenance Support Workspace

• Development, Integration and Test Support Workspace

• Operations Area ( IDSN Ops facility)

ISSDC

POC

Chandrayaan-1 Ground Segment PAYLOAD OPERATIONS

Ephemeris

Events

PVAT

Command Acknowledgement

Instrument Telemetry (P/L data)

Instrument House keeping

OBT - UT

File-ready Notification email

Command Messages

Products & E-mail

notification

SCC

Cmd Request

messages

Processed QLD

input

Archived PVAT

OBT-UT Ref.

Ephemeris

Events

Cmd schedule

Pass schedule

Instrument health

DSN

Bangalore –

18 / 32 m

S-LBT (RT- 2)

S-LBT (Dwell)

X-LBT (PB – SSR#2)

Remote View (SSR #2)

S-Band Tracking data

TC Ack

P/L Raw Data: TMC – APS 1, 2,

3, HySI, LLRI, HEX, C1XS, M3,

SIR-2, SARA, MIP, RADOM

SS + Gyro data (SSR #2)

TC

Schedule file

OVERALL DATA FLOW DIAGRAM

1.TMC & HysI - SAC

2.LLRI - ISAC

3.HEX - PRL

4.CIXSA - RAL

5.CIXSB - ISAC

6.SIR-2 – Max

Planck, Germany

7.SARA - VSSC

8.miniSAR - APL

9.M3 - JPL

EXTERNAL DSN

Bearslake

APL

NASA

P/L raw data

Look angles

Tracking data

LBT (RT + Dwell)

Lunar DEM Generation

Global DEM generation from TMC triplet

More than 100000 image triplets

Grid interval size ~25-50m

LLRI data use to be explored

ISRO Moon Atlas

• Cover the entire moon surface at Uniform Scale

(1:25,000/50,000)

• Consists of TMC & HySl Image and Image mosaics

• Contains Digital Elevation Model derived from TMC

• Softcopy & Hardcopy both

• Vector and Raster databases

High level Data products

The high level data products from the AO payloads are

Near Infra-red Spectrometer (SIR-2)

Spectroscopic data corrected for dark bias and bad pixel data

Radiometric and wavelength corrected data

Details of lunar surface in various geological, mineralogical

and topographical units

Sub-keV Atom Reflecting Analyser (SARA)

Images of energetic neutral atom distributions for specific

energy and mass group and time-dependent plots of total

fluxes for them (CENA)

Energy spectra for the four specified mass group atoms

Linear plot of proton fluxes(SWIM)

High level Data products (contd.)

Miniature Synthetic Aperture Radar (MiniSAR)

• Level 1 products ortho-rectified and resampled into oblique map

projections

• Four mosaics composed of multiply acquired data sets produced for

regions above 80º lunar latitude using level2 stokes parameters

Moon Mineralogy Mapper (M3)

• Radiance at sensor and seleno-corrected spectral image cubes

• Reflectance data

Radiation Dose monitor Experiment (RADOM)

• Estimated radiation dose equivalent from GCR,SPE and radiation

dose maps around moon

• Moon environment characteristics

• Elemental composition and Mineral Maps:M3,SIR-2,HySI, C1XS,SARA

• DEM from TMC with LLRI topo map

• Magnetic anomaly map of SARA with TMC base map

• Polar region map from MiniSAR, LLRI overlaid with TMC base map

• Projection of X-ray line abundances from C1XS and HEX against DEM

made from fusion of TMC and LLRI data

• Fusion of mineral map, elemental composition map with topographic map

• Integration of data from earlier lunar missions with that of Chandrayaan-1

Possible Fusion Data Products

Visualization tools and other utilities

Intended for public outreach and awareness.

Tool would show at a given point of time, how much imaging is done on the

globe of Moon.

Overlay of processed data showing the information layers available for

various instruments

Data Fusion (R&D)and other utilities

(in the form of software)

User can generate fusion products using the utilities provided at ISSDC

(generated by science teams or data processing teams) with required data

download facility. This also includes visualization tools for looking at a

particular area of interest

Education and Outreach Activity Plan

Comprehensive education and public outreach programme is under

development

Activities aimed towards a broad range of ages and abilities

Education and Public Outreach programme planned in four

categories

Formal education

• As part of basic curriculum for high school level students, providing

resource and support material-this is a long term strategy / plan

• Scientific research at university level (e.g. PLANEX Programme of

ISRO)

Semi-formal education

• Introducing project work as part of school curriculum (similar to that in

for B.Tech)

• ISRO may provide tool kits (involvement of industries)

Education and Outreach Activity Plan (contd.)

Informal Education

• Seminar, talks on Moon,Chandrayaan-1

• Essay contest

• Exhibition

• Team with local planetary society members, amateur observers /sky watchers-

to share and exchange ideas

• Use website

• Moon globe on website –similar to Google-Earth using TMC DEM

Public Outreach

• Popular publication

• Broadcast over national and local Radio and Television Network

• Use of Website

• For common public cultural, mythological and historical stories related to Moon

Education and Outreach Activity Plan (contd.)

A few sample questions which may be considered as project topic:

• Calculate distance between scale models of Earth and Moon

• To learn about locations and geology of sites identified by

• Chandrayaan-1 science team

• Compare the process of regolith formation on the Moon and the

relative process on Earth

• Design a spacecraft for going to moon and choose a landing site

of interest

• Construct a model of lunar rover

• Future lunar mission ideas

Outreach Implementation Plan

The outreach activity would be implemented in steps

• Mission update on ISRO/ Chandrayaan-1 Website from T-90 day

• Announcement of Opportunities towards Formal and Informal

Outreach activities seeking proposals from different groups

Collaborative agencies would be selected from Research

Laboratories,School, Colleges, Universities, National and Regional

science museums and Planetariums based on the activities

• After obtaining approval from DOS/ISRO, activities would be

carried out and monitored in collaboration with P & PR Unit ISRO

To Conclude – Why to go to Moon…

The first, of course, the scientific goals that despite many

missions of the past, the question of origin and evolution

of Moon still remains unanswered

The second objective is the challenges posed by

technology and mission planning

The third factor is such a mission can inspire the new

generation by the sheer excitement that such a flag-ship

mission will evoke.

India cannot afford to lose out in its ability to pursue

exploration