Sanitation Requirements in Space:

The issues of Space Debris and its Management

V. Adimurthy

Indian Space Research Organisation

“..we must be second to none in the application of advanced technologies to the real problems of man

and society.”

November 21, 1963

SLV-3 ASLV

TODAY, 2008

PSLV GSLV

ARYABHATA19.04.75

GSAT-208.05.03

KALPANA-112.09.02

INSAT-2E03.04.99

INSAT-3B22.03.00

INSAT-3A10.04.03

IRS-1C28.12.95

IRS-P321.03.96

IRS-1D29.09.97

RESOURCESAT-117.10.03

INSAT-3E28.09.03

TES22.10.01

INSAT-3C24.01.02

IRS-P426.05.99

Self reliance in launching

Self reliance in building satellites

48+ 7 Spacecraft Missions 10

4

FOUR DECADES OF INDIAN SPACE PROGRAMME

LA

UN

CH

VEH

ICLE

SA

TELLIT

E

AP

PLIC

ATIO

NS

25Launch Vehicle Missions

EDUSAT20.09.04

HAMSAT05.05.05

CARTOSAT-105.05.05

INSAT 4A

CARTO-2

November 21, 1963

SLV-3 ASLV

TODAY, 2008

PSLV GSLV

ARYABHATA19.04.75

GSAT-208.05.03

KALPANA-112.09.02

INSAT-2E03.04.99

INSAT-3B22.03.00

INSAT-3A10.04.03

IRS-1C28.12.95

IRS-P321.03.96

IRS-1D29.09.97

RESOURCESAT-117.10.03

INSAT-3E28.09.03

TES22.10.01

INSAT-3C24.01.02

IRS-P426.05.99

Self reliance in launching

Self reliance in building satellites

51 + 7 Spacecraft Missions 10

4

FOUR DECADES OF INDIAN SPACE PROGRAMME

LA

UN

CH

VEH

ICLE

SA

TELLIT

E

AP

PLIC

ATIO

NS

26 Launch Vehicle Missions

EDUSAT20.09.04

HAMSAT05.05.05

CARTOSAT-105.05.05

INSAT 4A

CARTO-2

Tele-Education Tele- Medicine

Trans LunarInjection

Mid Course Corrections

EPO 1

EPO 2 / 3 / 4

Lunar Transfer Trajectory at burn 5

Initial moon Orbit ~ 500 X 7500 km

Lunar InsertionManeuver

8th Nov 2008

Final Orbit 100 km PolarBy 13th Nov

ASTROSAT

Moon at Launch

PSLV –C11 22nd Oct 06:40 hrs EPO of 255 x 22,932 kmBurn # 1 23rd Oct 09:22 hrs EPO of 305 x 37,719 kmBurn # 2 25th Oct 06:03 hrs EPO of 336 x 74,716 kmBurn # 3 26th Oct 07:18 hrs EPO of 348 x 1,65,016 kmBurn # 4 29th Oct 07:41 hrs EPO of 459 x 2,66,611 kmBurn # 5 4th Nov 04:59 hrs EPO of 972 x 3,79,856 km

Lunar Orbital mass of 610 kg with 2 year life time.Scientific payload 55 kg +MIP 35 kg

Expanding the scientific knowledge about the moon, upgrading India’s technological capability

and providing challenging opportunities for planetary research for the younger generation

CHANDRAYAAN-1

MIP experiment 14th Nov

Chandrayaan 2:A Soft landing Mission to Moon

A minimum Soft Lander configuration requires 300 kg including Propellant. Operational duration 2 weeks.

With a rover the total mass is can be 400 kg

New technologies related to NGC, TTC, landing gear, robotics, thermal management in Lunar environment etc need to be developed for this mission

Wheels

Solar panel

Stereoscopic cameraAntenna

Chassis & suspension

Manipulator arm

Indian Lunar Rover (VIKRAM)

Wheels

Solar panel

Stereoscopic cameraAntenna

Chassis & suspension

Manipulator arm

Indian Lunar Rover (VIKRAM)

De-orbit

100 km

Transfer orbit (100 km x 15 km)

2-Point BVP

Solution by CRS

Moon

Optimal Design Parameters for 285 kg mass(Thrust = 440 N )

Maximum Landing Mass = 143 kg Minimum Fuel Consumed = 142 kg

15 km Horizontal breaking phase

Moon

3 km;Vertical descent phase

De-orbit

100 km

Transfer orbit (100 km x 15 km)

2-Point BVP

Solution by CRS

Moon

Optimal Design Parameters for 285 kg mass(Thrust = 440 N )

Maximum Landing Mass = 143 kg Minimum Fuel Consumed = 142 kg

15 km Horizontal breaking phase

Moon

3 km;Vertical descent phase

15 km Horizontal breaking phase

Moon

3 km;Vertical descent phase

A Concept of Indian Manned Space ProgrammeA Concept of Indian Manned Space Programme

MotivationMotivation

• Resources/Energy

Mining the Moon, planets and asteroids

• Scientific

Basic research in physical and life sciences

• Manufacturing / Industrial growth

New materials, pharmaceutical products

Human Presence in Space

gives the versatility to

achieve the above

ESCAPE

SYSTEM

CREW MODULE

SERVICE MODULE

ESCAPE

SYSTEM

CREW MODULE

SERVICE MODULE

GSLV MkII(4L40+S139)+ L37.5+

C12 + Orbital vehicle + Escape system

ConceptConcept

Typical Intake and effluent mass budget of Space Crew

•Carbon Dioxide = 1.00 kg

•Respiration & Perspiration Water = 2.28 kg

•Urine = 1.50 kg

•Feces water = 0.091 kg

•Urine solids = 0.059

•Feces solid = 0.032 kg

•Sweat solid = 0.018 kg

Oxygen = 0.84 kg

Food solids = 0.62 kg

Water (Drink) = 1.62 kg

Water in food = 1.50 kg

Metabolised water = 0.40 kg

(per person per day)

TOTAL = 4.98 kg

TOTAL = 4.98 kg

Short duration mission

‘Open cycle’ ECLSSOpen cycle’ ECLSSAll required resources for the crew provided from storage and stores the waste

generated without any re-cycling

Typical Space Toilet Typical Space Toilet SystemsSystems

Aggressive Growth of microorganisms in Space Environment

Reference Space

Early Ammonia Servicer (EAS) Mounted on the exterior of ISS was dumped into space in July 2007

The Waste Products from Spacecraft may be dumped out into

empty space generating Space Debris

•Campaign Started on 22nd October 2008

•Object chosen was Early Ammonia Servicer (Catalogue No. 31928) jettisoned from International Space Station in July, 2007. Mass of 640 kg, and dimensions of 2.5m x 1.2m x 1.7m. Inclination 51.64 deg

IADC Re-Entry Campaign 09 – 2008

Sl No.

Agency

Last Prediction with TLE on 03/11/08

TLE Epoch (UTC)

Prediction (UTC)

Error in

minutes

1 FSA, Russia2008/11/03

03:412008/11/03

05:068

2 ISRO, India2008/11/ 03

03:412008/11/ 03

04:4711

3 ESA2008/11/03

03:412008/11/03

04:4414

4CNSA, China

2008/11/03 01:08

2008/11/03 05:14

16

5 ASI, Italy2008/11/03

02:142008/11/03

04:3127

6 NASA, USA2008/11/03

02:142008/11/03

04:3127

7DLR,

Germany*---- ----- ----

8CNES,

France*----- ----- ----

9 BNSC, UK* ---- ----- ----

10JAXA, Japan*

---- ---- ----

24 26 28 30 32 34 361

1.5

2

2.5

3

3.5

4

4.5

5

5.5

TLE epoch No of Days from October 1, 2008Pre

dic

tio

n E

po

ch n

o. o

f D

ays

fro

m N

ove

mb

er 1

, 200

8 Prediction by VSSC

Reentry occurred on 03rd November 04:58 (UTC)

* did not make prediction on last day

An Overview of Space Debris Environment

Solid Motor Firing

Launch of Upper Stages & Payloads

Fragmentation

Collisions

Release of Na-K Coolant

Ejecta

Decay through Drag, Luni-solar Gravity, Solar

Radiation Pressure

Active Removal

Transfer to Disposal

Orbit

Fragments ~ 6400

Spacecrafts ~ 3100

Rocket Bodies ~ 1600

Mission Related Objects ~ 1500

Debris

N ~ 1010 d 0.1 mm

N ~ 105 d 1 cmNot Trackable

Tra

cke

d &

C

atal

og

ue

d

Source Sink

Space Debris refers to material that is on orbit as the result of space initiatives, but is no longer serving any useful function.

Est

ima

ted

94% of Tracked Object Population are Debris. > 0.1 mm : ~ 1010 (Estimated)

> 1 cm : ~ 105 (Estimated) > 10 cm : ~ 104 (Trackable)

N ~

104

: d

1

0 cm

Evolution of Space Debris Environment

200719971987197719671957

12000

9000

6000

3000

0

15000

Cat

alo

gu

ed

Sp

ace

Ob

ject

s

2008

Fragments~ 6400

Spacecraft ~ 3100

L/V Stages ~ 1600

Mission Debris ~

1500

Growth of Catalogued Space Object Population during 1957-2008

2007

Total

Spacecrafts

Mission DebrisL/V Stages

Fragments

Protected Regions & Debris Mitigation Measures

GSO Altitude

15°

2000 km 200 km200 km

Limit the Release of Operational Debris

Space Debris Risk Mitigation Measures

On-orbit Collision Prevention

Proximity AvoidanceAvoid Intentional Fragmentation

Minimize Potential for On-orbit Breakup

Deorbiting/Reentry Lifetime Limitation

Post Mission Disposal

Reorbiting

Protected Region AProtected Region B

Passivation

IADC Space Debris Mitigation Guidelines

PSLV-C11/Chandrayaan-1 MissionSpace Object Proximity Analysis

Launch Date : 22 Oct 2008

Lift Off not Recommended in Time Intervals MarkedMaximum (Worst Case) Collision Probability Estimated to be More than 1×10-6 for PSLV-C11 (in ascent Phase) and 1×10-5 (Till the 1st Apogee after Injection) for Chandrayaan-1

56 57 58 595550 51 52 534944 45 46 474338 39 40 413732 33 34 353130 36 42 48 54 00

06:40:0001:10:00

06:35:0001:05:00

06:45:0001:15:00

06:50:0001:20:00

07:00:0001:30:00

IST : 06:30:00UTC : 01:00:00

06:55:0001:25:00

26 27 28 292520 21 22 231914 15 16 171308 09 10 110702 03 04 050100 06 12 18 24 30

06:10:0000:40:00

06:05:0000:35:00

06:15:0000:45:00

06:20:0000:50:00

06:30:0001:00:00

IST : 06:00:00UTC : 00:30:00

06:25:0000:55:00

Launch Window Starts

Lift Off Time

Nominal Launch Window Ends Debris (0.7 km) R/B (0.8 km)

Some of the Recovered Orbital Debris upon Reentry

Safe Zone forControlled Reentry

Delta-II 2nd Stage Tank

Delta-II 2nd Stage Tank

Woven Materials from Delta-II

Foton Pressure Vessel

Delta-II 3rd Stage Motor Case

Atlas Parts

Thank You