sanitation requirements in space: the issues of space debris and its management v. adimurthy indian...
Post on 27-Dec-2015
234 Views
Preview:
TRANSCRIPT
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
top related