बुधवार, 31 अक्तूबर 2012

Satellites



For the past four decades, ISRO has launched more than 100 satellites for various scientific and technological applications like mobile communications, Direct-to-Home services, meteorological observations, telemedicine, tele-education, disaster warning, radio networking, search and rescue operations, remote sensing and scientific studies of the space.
ISRO has established two major space systems, the Indian National Satellite System (INSAT) series for communication, television broadcasting and meteorological services which is Geo-Stationary Satellites, and Indian Remote Sensing Satellites (IRS) system for resources monitoring and management which is Earth Observation Satellites. ISRO has launched many Experimental Satellites which are generally small comparing to INSAT or IRS and Space Missions to explore the space.

Geo-Stationary Satellites:

GSAT-10:-
GSAT-10, India’s advanced communication satellite, is a high power satellite being inducted into the INSAT system. Weighing 3400 kg at lift-off, GSAT-10 is configured to carry 30 communication transponders in normal C-band, lower extended C-band and Ku-band as well as a GPS Aided GEO Augmented Navigation (GAGAN) payload operating in L1 and L5 bands. GSAT-10 is the second satellite to carry GAGAN payload after GSAT-8, which is already providing navigation services from orbit. GSAT-10 also carries a Ku-band beacon to help in accurately pointing ground antennas towards the satellite.

The 30 communication transponders onboard GSAT-10 will further augment the capacity in the INSAT system. The GAGAN payload provides the Satellite Based Augmentation System (SBAS), through which the accuracy of the positioning information obtained from the GPS satellites is improved by a network of ground based receivers and made available to the users in the country through geo-stationary satellites.

PAYLOADS OF GSAT-10 COMMUNICATION PAYLOADS
  • 12 Ku-band transponders each with 36 Mhz usable bandwidth employing 140 W Travelling Wave Tube Amplifier (TWTA) with footprint covering Indian mainland with an Edge of Coverage Effective Isotropic Radiated Power (EIRP) of 51.5 dBW and Andaman & Nicobar islands with an EIRP of 49.5 dBW
  • 12 C-band transponders each with 36 MHz usable bandwidth employing 32 W TWTA with footprint covering Indian mainland and West Asia with an Edge of Coverage EIRO of 40 dBW
  • 6 Lower Extended C-band transponders each with 36 MHz usable bandwidth employing 32 W TWTA with footprint covering Indian mainland and island territories with an Edge of Coverage EIRP of 38 dBW and 37 dBW respectively 

NAVIGATION PAYLOAD

Mission
Communication
Weight
3400 kg (Mass at Lift – off)
1498 kg (Dry Mass)
Power
Solar array providing 6474 Watts (at Equinox) and two 128 AH Lithium-Ion batteries
Physical Dimensions
2.0 m X 1.77 m X 3.1 m cuboid
Propulsion
440 Newton Liquid Apogee Motors (LAM) with Mono Methyl Hydrazine (MMH) as fuel and Mixed oxides of Nitrogen (MON-3) as oxidizer for orbit raising.
Satbilisation
3-axis body stabilised in orbit using Earth Sensors, Sun Sensors, Momentum and Reaction Wheels, Magnetic Torquers and eight 10 Newton and eight 22 Newton bipropellant thrusters
Antenns
East : 2.2 m dia circular deployable Dual Gridded Reflector (DGR)
West : 2.2 m X 2.4 m elliptical deployable DGR
Earth Viewing Face (top) : 0.7 m parabolic, 0.9 m parabolic and 0.8 m X 0.8 m sixteen element helical antenna for GAGAN
Launch date
September 29, 2012
Launch site
Kourou, French Guiana
Launch vehicle
Ariane-5 VA-209
Orbit
Geostationary (83° East longitude), co-located with INSAT-4A and GSAT-12
Mission life
15 Years
  • Two-channel GAGAN payload operating in L1 and L5 bands provides Satellite-based Navigation services with accuracy and integrity required for civil aviation applications over Indian Air Space. 


GSAT-12:
GSAT-12, the latest communication satellite built by ISRO, weighs about 1410 kg at lift-off. GSAT-12 is configured to carry 12 Extended C-band transponders to meet the country's growing demand for transponders in a short turn-around-time.

The 12 Extended C-band transponders of GSAT-12 will augment the capacity in
Mission
Communication
Weight
1410 kg (Mass at Lift – off)
559 kg (Dry Mass)
Power
Solar array providing 1430 Watts and one 64 Ah Li-Ion batteries
Physical Dimensions
1.485 x 1.480 x 1.446 m cuboid
Propulsion
440 Newton Liquid Apogee Motors (LAM) with Mono Methyl Hydrazine (MMH) as fuel and Mixed oxides of Nitrogen (MON-3) as oxidizer for orbit raising.
Attitude Orbit Control
3-axis body stabilised in orbit using Earth Sensors, Sun Sensors, Momentum and Reaction Wheels, Magnetic Torquers and eight 10 Newton and eight 22 Newton bipropellant thrusters
Antennae
One 0.7 m diameter body mounted parabolic receive antenna and one 1.2 m diameter polarisation sensitive deployable antenna
Launch date
July 15, 2011
Launch site
SHAR, Sriharikota, India
Launch vehicle
PSLV-C17
Orbit
Geosynchronous (83° longitude)
Mission life
About 8 Years
the INSAT system for various communication services like Tele-education, Telemedicine and for Village Resource Centres (VRC). 


            GSAT-8
GSAT-8, India’s advanced communication satellite, is a high power communication satellite being inducted in the INSAT system. Weighing about 3100 Kg at lift-off, GSAT-8 is configured to carry 24 high power transponders in Ku-band and a two-channel GPS Aided Geo Augmented Navigation (GAGAN) payload operating in L1 and L5 bands.
The 24 Ku band transponders will augment the capacity in the INSAT system. The GAGAN payload provides the Satellite Based Augmentation System (SBAS), through which the accuracy of the positioning information obtained from the GPS Satellite is improved by a network of ground based receivers and made available to the users in the country through the geostationary satellites
.

Mission
Communication
Weight
3093 kg (Mass at Lift – off)
1426 kg (Dry Mass)
Power
Solar array providing 6242 watts three 100 Ah Lithium Ion batteries
Physical Dimensions
2.0 x 1.77 x 3.1m cuboid
Propulsion
440 Newton Liquid Apogee Motors (LAM) with mono Methyl Hydrazine (MMH) as fuel and Mixed oxides of Nitrogen (MON-3) as oxidizer for orbit raising.
Stabilisation
3-axis body stabilised in orbit using Earth Sensors, Sun Sensors, Momentum and Reaction Wheels, Magnetic Torquers and eight 10 Newton and eight 22 Newton bipropellant thrusters
Antennas
Two indigenously developed 2.2 m diameter transmit/receive polarisation sensitive dual grid shaped beam deployable reflectors with offset-fed feeds illumination for Ku-band; 0.6 m C-band and 0.8x0.8 sq m L-band helix antenna for GAGAN
Launch date
May 21, 2011
Launch site
Kourou, French Guiana
Launch vehicle
Ariane-5 VA-202
Orbit
Geosynchronous (55° E)
Mission life
More Than 12 Years

GSAT-5P:                                                          
Launch Date
- 25.12.2010

GSAT-5P was the fifth satellite launched in the GSAT series. It was an exclusive communication satellite to further augment the communication services currently provided by the Indian National Satellite (INSAT) System. Weighing 2310 kg at lift-off, GSAT-5P carried 24 Normal C-band and 12 Extended C-band transponders.

However, GSAT-5P was not placed in orbit as GSLV-F06 could not complete the mission.


GSAT-4
Launch Date-
5.04.2010
GSAT-4 was the nineteenth geo-stationary satellite of India built by ISRO and fourth in the GSAT series. GSAT-4 was basically an experimental satellite with the following new technologies intended to be tested:
·                     Electric Propulsion System
·                     Bus Management Unit
·                     1553 Bus for Data Communication
·                     Miniaturised Dynamically Tuned Gyros
·                     36 AH Lithium Ion Battery
·                     70 V Bus for Ka band TWTAs
However, GSAT-4 was not placed in orbit as GSLV-D3 could not complete the mission.
                                                                                                                                                                                                                                                                                                 
INSAT-4CR:
INSAT–4CR spacecraft is configured with exclusive Ku band employing the I-2K bus with a mass of 2130 Kg. It was injected into the orbit by GSLV-F04 rocket with enhanced Russian Cryogenic engine and co-located at 74o East longitude along with INSAT–3C / Kalpana–1 / GSAT–3 (EDUSAT).
INSAT-4CR carries 12 high-power Ku-band transponders designed to provide Direct-to-home (DTH) television services, Video Picture Transmission (VPT) and Digital Satellite News Gathering (DSNG). 


Mission
Communication
Weight
2,130 kg (Mass at Lift – off)
Onboard power
3000 W
Communication Payload
12 Ku-band transponders employing 140 W Traveling Wave Tube Amplifiers (TWTA)
Ku-band Beacon
Launch date
September 2, 2007
Launch site
SHAR, Sriharikota, India
Launch vehicle
GSLV-F04
Orbit
Geosynchronous (74° E)
Mission life
12 Years

          INSAT–4B:
INSAT–4B Spacecraft is the second in the INSAT 4 series of spacecrafts and is configured with exclusive communication payloads to provide services in Ku and C frequency bands. This is co-located with INSAT–3A at 93.5 o E longitude.


Mission
Communication
Weight
3025 Kg (at Lift – off)
Onboard Power
5859 W
Stabilization
It uses 3 earth sensors, 2 digital sun sensors, 8 coarse analog sun sensors, 3 solar panel sun sensors and one sensor processing electronics. The wheels and wheel drive electronics were imported with indigenous wheel interface module to interface the wheel drive electronics and AOCE.
Propulsion
The propulsion system is employing 16 thrusters, 4 each located on east, west and AY sides and 2 each on north and south sides. There is one 440 N liquid apogee motor (using Mono Methyl Hydrazine (MMH) as fuel and oxides of Nitrogen ( MON3 as oxidizer) and three presurant tanks mounted on the LAM deck.
Payload
12 Ku band high power transponders covering Indian main land using 140W radiatively cooled TWTAs.
12 C band high power transponders with extended coverage, covering southeast and northwest region apart from Indian main land using 63 W TWTAs
Launch date
 March 12, 2007
Launch Site
French Guyana
Launch Vehicle
 Ariane5
Orbit
Geostationary (93.5o E Longitude)
Mission Life
 12 Years

INSAT-4C
Launch Date-
10.07.2006
India's Geosynchronous Satellite Launch Vehicle (GSLV-F02), with INSAT-4C on board, was launched from Satish Dhawan Space Centre SHAR (SDSC SHAR), Sriharihota on July 10, 2006. However, GSLV-F02 could not complete the mission.



INSAT-4A:

INSAT-4A, first in INSAT-4 Satellites series provides services in Ku and C-band frequency bands. The Ku transponders cover the Indian main land and C-Band transponders cover an extended area. It has a dozen Ku transponders and another dozen of C-band transponders. This spacecraft is placed at 83o E along with INSAT-2E and INSAT-3B, by Ariane launch vehicle (ARIANE5-V169).
 


Spacecraft Mass
Lift off 3081 Kg
Dry Mass 1386.55 Kg
Orbit
Geostationary ( 83o E)
Power
Solar Array to provide a power of 5922 W
Battery
Three 70 Ah Ni H2 Batteries for eclipse support of 4264 W
Life
12 Years
Launch date
December 22, 2005
Launch vehicle
ARIANE5-V169

HAMSAT

HAMSAT is a Micro-satellite for providing satellite based Amateur Radio services to the national as well as the international community of Amateur Radio Operators (HAM). It consists of two transponders-one indigenously developed by Indian Amateurs, with the expertise of ISRO and the experience of HAMSAT-INDIA. The second transponder has been developed by a Dutch Amateur Radio Operator and Graduate Engineering student at Higher Technical Institute, Venlo, The Netherlands.


Launch date
May 5, 2005
Launch site
SHAR Centre, Sriharikota, India
Launch vehicle
PSLV-C6
Orbit
Geo-synchronous, 633.355 km (average)
Payloads
2 Transponders

EDUSAT:

GSAT-3, known as EDUSAT is meant for distant class room education from school level to higher education. This is the first dedicated "Educational Satellite" that provide the country with satellite based two way communication to class room for delivering educational materials.
This is a Geo-synchronous satellite developed on I-2K bus. GSAT-3 is co-located with METSAT(KALPANA-1) and INSAT-3C at 74o E longitude. 


Mission
Education
Spacecraft Mass
1950.5 Kg mass (at Lift - off)
819.4 Kg (Dry mass)
Onboard power
Total four solar panel of size 2.54 M x 1.525 M generating 2040 W (EOL), two 24 AH NiCd batteries for eclipse support
Stabilization
3 axis body stabilised in orbit using sensors, momentum and reaction wheels, magnetic torquers and eight 10 N & 22N reaction control thrusters.
Propulsion
440 N Liquid Apogee Motor with MON - 3 and MMH for orbit raising
Payload
  • Six upper extended C - band transponders
  • Five lower Ku band transponders with regional beam coverage
  • One lower Ku band National beam transponder with Indian main land coverage
  • Ku beacon
  • 12 C band high power transponders with extended coverage, covering southeast and northwest region apart from Indian main land using 63 W LTWTAs
Launch date
September 20, 2004
Launch site
SHAR, Sriharikota, India
Launch vehicle
GSLV-F01
Orbit
Geostationary (74oE longitude)
Mission Life
7 Years (minimum)



INSAT-3E
INSAT-3E is the fourth satellite launched in the INSAT-3 series. It is an exclusive communication satellite to further augment the communication services that are being provided by the INSAT System. Weighing 2775 kg at lift-off, INSAT-3E carries 24 Normal C-band and 12 Extended C-band transponders.
Mission
Communication
Spacecraft Mass
2,775 Kg (Mass at Lift-off)
1218 Kg (Dry mass)
Launch date
September 28, 2003
Launch site
French Guyana
Launch vehicle
Ariane5-V162

GSAT-2:

GSAT-2 is a 2000 kg class experimental communication satellite onboard the second developmental test flight of India's Geosynchronous Satellite Launch Vehicle, GSLV-D2. The satellite carries four C-band transponders, two Ku-band transponders and a Mobile Satellite Service (MSS) payload operating in S-band and C-band for forward link and return link respectively.

GSAT-2 also carries four scientific experimental payloads - Total Radiation Dose Monitor (TRDM), Surface Charge Monitor (SCM), Solar X-ray Spectrometer (SOXS) and Coherent Radio Beacon Experiment (CRABEX).

Mission
Communication
Weight
1800 Kg
Launch date
May 8, 2003
Launch site
SHAR, Sriharikota, India
Launch vehicle
GSLV–D2
Orbit
Geostationary orbit (48oE longitude)

Kalpana – 1:

METSAT (renamed as Kalpana - 1 on February 5, 2003 after the Indian born American Astronaut Dr. Kalpana Chawla, who died on February 1, 2003 in the US Space Shuttle Columbia disaster) is the first in the series of exclusive meteorological satellites built by ISRO. 


Mission
Meteorological
Spacecraft Mass
  • 1060 Kg mass (at Lift – off)
  • 498 Kg (Dry mass)
 Onboard Power
  550 W
Payload
Very High Resolution Radiometer (VHRR)
Data Relay Transponder (DRT)
Launch date
12 September 2002
Launch site
SHAR, Sriharikota
Launch vehicle
PSLV – C4
Orbit
Geostationary (74 deg East longitude)
Mission
7 Years

INSAT-3C:

INSAT-3C, carrying Fixed Satellite Services (FSS) transponders, Broadcast Satellite Services (BSS) transponders and Mobile Satellite Services (MSS) transponders is intended to continue the service of INSAT-2DT and INSAT-2C which were nearing their end to life besides improving and augmenting the INSAT system capacity. INSAT-3C is the second satellite of the INSAT-3 series. The first satellite, INSAT-3B was launched in March 2000.


Mission
Communication, broadcasting and Meteorology
Spacecraft Mass
2,650 Kg (Mass at Lift - off)
1218 Kg (Dry mass)
Onboard power
2765 W
Propulsion
Liquid Apogee Motor with fuel and oxidizer stored in separate titanium tanks and pressurant in Kevlar wound titanium tank.
Payload
  • 24 C band transponders
  • 6 Extended C - band Transponders
  • 2 S - band Transponders
Launch date
January 24, 2002
Launch site
French Guyana
Launch vehicle
Ariane5-V147
Orbit
Geostationary (74o longitude)
Mission Life
Very long

GSAT-1:

GSAT-1 carrying three C-band transponders and one S-band transponder was launched on April 18, 2001 by GSLV-D1. GSAT-1 is used for conducting communication experiments like digital audio broadcast, internet services and compressed digital TV transmission. Several new spacecraft elements like improved reaction control thrusters, fast recovery star sensors and heat pipe radiator panels were also tested on this satellite.

Mission
Communication
Weight
1530 Kg
Launch date
18 April 2001
Launch site
SHAR, Sriharikota
Launch vehicle
GSLV – D1
Orbit
Sun Synchronous Geo stationary orbit



INSAT-3B:

INSAT – 3B is the first of the five ISRO built satellites under INSAT – 3 series to join INSAT system. INSAT – 3B is collocated with INSAT – 2E at 83 deg East Longitude. This satellite primarily serves to business communication, mobile communication and developmental communication;

it provides the first set to transponders for Swaran Jayanti Vidya Vikas Antariksh Upagraha Yojana (Vidya Vahini) for interactive training and developmental communication giving fillip to the training and developmental Communication channel of INSAT.


Mission
Communication and Meteorology
Spacecraft Mass
  • 2,070 (Mass at Lift – off)
  • 970 Kg (Dry mass)
Onboard power
1,712 W
Stabilization
3 – axis body stabilised biased momentum control system using earth sensors, sun sensors, inertial reference unit, momentum / reaction wheels, magnetic torquers and unified bi-propellant thrusters.
Propulsion
Liquid Apogee Motor with fuel and oxidizer stored in separate titanium tanks and pressurant in Kevlar wound titanium tank.
Payload
  • 12 extended C – band Transponders
  • Five Ku band Transponders
  • Mobile Satellite Services (MSS)
Launch date
22nd March 2000
Launch site
French Guyana
Launch vehicle
Ariane -5
Orbit
Geostationary (83 deg East longitude)
Inclination
7 deg
Mission
Very long


INSAT-2E:

INSAT - 2E, the last of the INSAT -2 series of satellites built by ISRO, is a multi - purpose satellite for telecommunication, television broadcasting and meteorological services.

The very High Resolution Radiometer will operate in three spectral bands with 2 km resolution in visible band and 8km resolution in thermal infrared and water vapour bands. The water vapour band has been introduced in the INSAT system for the first time. In addition, INSAT - 2E will also carry a Charge Coupled Device Camera, again for the first time in the INSAT. This camera will also operate in three spectral bands - visible, near infrared and short wave infrared - providing a spatial resolution of 1 km.
Mission
Communication and Meteorology
Spacecraft Mass
  • 2,550 Kg (Mass at Lift-off)
  • 1150 Kg (Dry mass)
Launch date
03 April 1999
Launch site
French Guyana
Launch vehicle
Ariane – 42P
Orbit
Geosynchronous (83 deg east longitude)

INSAT-2DT:                                                        
Launch Date
:Jan 1998


The three Arabsat 1 spacecraft are based on the Aerospatiale and MBB Spacebus-100 platform. Ranging from nearly 600 kg to almost 800 kg at the start of life in GEO, the spacecraft measure 1.5 m by 1.6 m by 2.3 m with a solar array span of about 21 m for 1.4 kW of electrical power. The primary communications payload consists of two S-band transponders and 25 C-band transponders. The nominal design life was seven years.







INSAT-2D:

Become Inoperable in October 1997 due to power bus anomaly.

Replaced by INSAT-2DT.


Mission
Communication
Weight
2079 kg with propellants, 995 kg dry weight
onboard power
1650 Watts
Communication
C,extended C, S and Ku bands
Stabilization
Three axis stabilized with two Momen'tum Wheels
& one Reaction Wheel,Magnetic torquers
Propulsion
Integrated bipropellan stystem ( MMH and N2 04) With sixteen 22N thrusters and 440N LAM.
Payload
Transponders:
16C-band / extended C-band transponders (forFSS),
2 high power C-band transponders (for BSS),
1S-band transponder (for BSS),1C/S-band mobile
communication transponder, 3 Ku-band transponders
Launch date
June 4, 1997
Launch site
French Guyana
Launch vehicle
Arianev 4
Orbit
Geostationary 93,.5deg.E
Inclination
0 deg.
Mission life
Seven years(nominal)
Orbit life
Very Long





INSAT-2C:

Power of four C-band transponders increased to improve communication facilities in remote areas like Northeast and Andaman & Nicobar Islands.

Coverage of two other C-band transponders is enlarged to include parts of southeast Asia, Central Asia and West Asia


Mission
Communication
Weight
2106kg with propellants 946 kg dry weight
Onboard power
1320 Watts
Communication
C extended C, S and Ku bands
Stabilization
Three axis stabilized with two Momen'tum Wheels
& one Reaction Wheel,Magnetic torquers
Propulsion
Integrated bipropellan stystem ( MMH and N2 04) With sixteen 22N thrusters and 440N LAM.
Payload
Transponders:
16C-band / extended C-band transponders (forFSS),
2 high power C-band transponders (for BSS),
1S-band transponder (for BSS),1C/S-band mobile
communication transponder, 3 Ku-band transponders
Launch date
December 7, 1995
Launch site
French Guyana
Launch vehicle
Ariane4
Orbit
Geostationary 93.5 deg E
Inclination
0 deg.
Mission life
Seven years(nominal)
Orbit life
Very Long



INSAT-2B:
Mission
Multi purpose Communication, meteorology and
Satellite based search and rescue
Weight
1906 kg with propellant
916 kg dry weight
Onboard power
One KW approx.
Communication
C, extended C and S band
Stabilization
Three axis body stabilized with two Momentum
Wheels & one Reaction Wheel, Magnetic torquers
Propulsion
Integrated bipropellant stystem ( MMH and N2 04) With sixteen 22 N thrusters and 440 N LAM.
Payload
Transponders:
12C-band (for FSS),6 ext. C-band (for FSS)
2S-band (for BSS),1Data relay transponder (for met.data), 1 transponder for research and rescue,
Very High Resolution radiometer (VHRR) for
meteorological observation with 2 km resolution in
the visible and 8 km resolution in the IR band
Launch date
July 23, 1993
Launch site
French Guyana
Launch vehicle
Ariane 4
Orbit
Geostationary 93.5o E
Inclination
0o
Mission life
Seven years(nominal)
Orbit life
Very Long

INSAT-2A:
First Multipurpose satellite built by India, Sucessfully Operationalised in August 1992.

Mission
Multi purpose Communication, meteorology and
Satellite based search and rescue
Weight
1906 kg with propellant 916 kg dry weight
Onboard power
One KW approx
Communication
C, extended C and S band
Stabilization
Three axis body stabilized with two Momentum
Wheels & one Reaction Wheel, Magnetic torquers
Propulsion
Integrated bipropellan stystem ( MMH and N2 04) With sixteen 22 N thrusters and 440 LAM.
Payload
Transponders:
12C-band (for FSS),6 ext. C-band (for FSS)
2S-band (for BSS),1Data relay transponder (for met.data), 1 transponder for research and rescue,
Very High Resolution radiometer (VHRR) for
meteorological observation with 2 km resolution in
the visible and 8 km resolution in the IR band
Launch date
July 10,1992
Launch site
French Guyana
Launch vehicle
Ariane 4
Orbit
Geostationary 74oE longitude
Inclination
0o
Mission life
Seven years(nominal)
Orbit life
Very Long

INSAT-1D:                                                                  
Launch Date
-12.06.1990

The specification for the Insat-1D is the same as the Insat-1B but with expanded battery and propellant capacities. Launched on 12 June 1990 to conclude the first generation Insat series.



INSAT-1C:                                                                  
Launch Date
 -21.07.1988

The Insat-1C satellite was launched on 21 July 1988 from Kourou for location at 93.5°E to bring the Insat system up to full capacity. Half of the 12 C-band transponders and its two S-band transponders were lost when a power system failure knocked out one of the two buses, but the meteorological earth images and its data collection systems were both fully operational.

INSAT-1B:
Launch Date
-30.08.1983


When Insat-1B was launched on 30 August 1983, it almost suffered the same fate as the Insat-1A. It was not until mid-September that Ford and Indian controllers succeeded in deploying its solar array. By then it had been stationed at 74°E in place of Insat-1A. Full operational capability was achieved in October 1983. It continued to operate into 1990 with all its 4375 two-way voice or equivalent circuits in use. Around 36,000 earth images were returned.


INSAT-1A:                                                                            
Launch Date
-10.04.1982
                           
The Insat-1A was launched by a Delta in April 1982 but was abandoned in September 1983 when its attitude control propellant was exhausted.







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