शुक्रवार, 2 नवंबर 2012

Earth Observation Satellites




Indian Remote Sensing (IRS) satellite system was commissioned with the launch of IRS-1A, in 1988. With twelve satellites in operation, IRS is the largest civilian remote sensing satellite constellation in the world providing imageries in a variety of spatial resolutions, spectral bands and swaths. The data is used for several applications covering agriculture, water resources, urban development, mineral prospecting, environment, forestry, drought and flood forecasting, ocean resources and disaster management.

RISAT-1:

Radar Satellite-1 (RISAT-1) is a state of the art Microwave Remote Sensing Satellite carrying a Synthetic Aperture Radar (SAR) Payload operating in C-band (5.35 GHz), which enables imaging of the surface features during both day and night under all weather conditions.

Application 

Active Microwave Remote Sensing provides cloud penetration and day-night imaging capability. These unique characteristics of C-band (5.35GHz) Synthetic Aperture Radar enable applications in agriculture, particularly paddy monitoring in kharif season and management of natural disasters like flood and cyclone. 

Lift-off Mass
1858 kg
Orbit
Circular Polar Sun Synchronous
Orbit Altitude
536 km
Orbit Inclination
97.552
Orbit Period
95.49 min
Number of Orbits per day
14
Local Time of Equator Crossing
6:00 am / 6:00 pm
Power
Solar Array generating 2200 W and one 70 AH Ni-H2 battery
Repetivity
25 days
Attitude and Orbit Control
3-axis body stabilised using Reaction Wheels, Magnetic Torquers and Hydrazine Thrusters
Nominal Mission Life
5 years
Launch date
April 26, 2012
Launch site
SDSC SHAR Centre, Sriharikota, India
Launch vehicle
PSLV- C19

 Megha-Tropiques:

Megha-Tropiques is an Indo-French Joint Satellite Mission for studying the water cycle and energy exchanges in the tropics. The main objective of this mission is to understand the life cycle of convective systems that influence the tropical weather and climate and their role in associated energy and moisture budget of the atmosphere in tropical regions.

Megha-Tropiques will provide scientific data on the contribution of the water cycle to the tropical atmosphere, with information on condensed water in clouds, water vapour in the atmosphere, precipitation, and evaporation. With its circular orbit inclined 20 deg to the equator, the Megha-Tropiques is a unique satellite for climate research that should also aid scientists seeking to refine prediction models.

Megha-Tropiques carries the following four payloads:
  • Microwave Analysis and Detection of Rain and Atmospheric Structures (MADRAS), an Imaging Radiometer developed jointly by CNES and ISRO
  • Sounder for Probing Vertical Profiles of Humidity (SAPHIR), from CNES
  • Scanner for Radiation Budget (ScaRaB), from CNES
  • Radio Occultation Sensor for Vertical Profiling of Temperature and Humidity (ROSA), procured from Italy

Lift-off Mass
1000 kg
Orbit
867 km with an inclination of 20 deg to the equator
Thermal
Passive system with IRS heritage
Power
1325 W (at End of Life)
Two 24 AH NiCd batteries
TTC
S-band
Attitude and Orbit Control
3-axis stabilised with 4 Reaction Wheels, Gyros and Star sensors, Hydrazine based RCS
Solid State Recorder
16 Gb
Launch date
October 12, 2011
Launch site
SDSC SHAR Centre, Sriharikota, India
Launch vehicle
PSLV- C18
RESOURCESAT-2:

RESOURCESAT-2 is a follow on mission to RESOURCESAT-1 and the eighteenth Remote Sensing satellite built by ISRO. RESOURCESAT-2 is intended to continue the remote sensing data services to global users provided by RESOURCESAT-1, and to provide data with enhanced multispectral and spatial coverage as well.
Important changes in RESOURCESAT-2 compared to RESOURCESAT-1 are: Enhancement of LISS-4 multispectral swath from 23 km to 70 km and improved Radiometric accuracy from 7 bits to 10 bits for LISS-3 and LISS-4 and 10 bits to 12 bits for AWIFS. Besides, suitable changes, including miniaturisation in payload electronics, have been made in RESOURCESAT-2.
RESOURCESAT-2 also carries an additional payload known as AIS (Automatic Identification System) from COMDEV, Canada as an experimental payload for ship surveillance in VHF band to derive position, speed and other information about ships.
RESOURCESAT-2 carries two Solid State Recorders with a capacity of 200 Giga Bytes each to store the images taken by its cameras which can be read out later to ground stations. 
Mission
Remote Sensing
Orbit
Circular Polar Sun Synchronous
Orbit altitude at injection
822 km + 20 km (3 Sigma)
Orbit Inclination
98.731º + 0.2º
Lift-off Mass
1206 kg
Orbit Period
101.35 min
Number of Orbits per day
14
Local Time of Equator crossing
10:30 am
Repetivity
24 days
Attitude and Orbit Control
3-axis body stabilised using Reaction Wheels, Magnetic Torquers and Hydrazine Thrusters
Power
Solar Array generating 1250 W at End Of Life, two 24 AH Ni-Cd batteries
Launch date
April 20, 2011
Launch site
SHAR Centre Sriharikota India
Launch vehicle
PSLV- C16
Mission life
5 years

 CARTOSAT - 2B :

CARTOSAT - 2B is the seventeenth satellite in the Indian Remote Sensing Satellite series (IRS). CARTOSAT-2B carries a Panchromatic camera (PAN) similar to those of its predecessors - CARTOSAT-2 and 2A. It is capable of imaging a swath (geographical strip) of 9.6 km with a resolution of better than 1 metre. The scene specific spot imagery sent by CARTOSAT-2B's PAN will be useful for cartographic and a host of other applications. The highly agile CARTOSAT-2B is steerable up to ± 26o along as well as across track to obtain stereoscopic imagery and achieve a four to five day revisit capability.

Mission
Remote Sensing
Weight
694 kg (Mass at lift off)
Onboard Orbit
930 Watts
Stabilization
3 – axis body stabilised based on inputs from star sensors and gyros using Reaction wheels, Magnetic Torquers and Hydrazine Thrusters
Payloads
Panchromatic Camera
Launch date
July 12, 2010
Launch site
SHAR Centre Sriharikota India
Launch vehicle
PSLV- C15
Orbit
630 kms, Polar Sun Synchronous
Inclination
97.71º

Oceansat-2:

Oceansat-2 satellite mainframe systems derive their heritage from previous IRS missions and launched by PSLV-C14 from Satish Dhawan Space Centre, Sriharikota on Sept. 23, 2009. It carries three payloads:
  • Ocean Colour Monitor (OCM)
  • Ku-band Pencil Beam scatterometer (SCAT) developed by ISRO
  • Radio Occultation Sounder for Atmosphere (ROSA) developed by the Italian Space Agency.
Oceansat-2 is envisaged to provide continuity of operational services of Oceansat-1(IRS-P4) with enhanced application potential.


Launch date
Sept 23, 2009
Launch site
SHAR, Sriharikota
Launch vehicle
PSLV - C14
Orbit
Polar Sun Synchronous
Altitude
720 km
Inclination
98.28°
Period
99.31 minutes
Local time of Eq. crossing
12 noon ± 10 minutes
Repetitivity cycle
2 days
Payloads
OCM, SCAT and ROSA
Mass at lift off
960 kg
Power
15 Sq.m Solar panels generating 1360W, Two 24 Ah Ni-Cd Battries
Mission Life
5 years

RISAT-2:

RISAT-2 is a Radar Imaging Satellite with all weather capability to take images of the earth. This Satellite will enhance ISRO's capability for Disaster Management applications.


Altitude
550 km
Inclination
41 deg
Orbit Period
90 minutes
Mass
300 kg


IMS-1:

IMS-1, previously referred to as TWSat (Third World Satellite), is a low-cost microsatellite imaging mission of ISRO (Indian Space Research Organization).


Orbit
Polar Sun Synchronous
Altitude
635 km
Mission Life
2 years
Physical Dimensions
0.604x0.980x1.129 m
Mass
83 kg
Power
Two deployable sun pointing solar panels generating 220 W power, 105 Ah Lithium ion battery
Telemetry, Tracking and Command
S-band
Atlitude and Orbit Control System
Star Sensor,
Miniature Sun Sensors, Magnetometers Gyros,
Miniature Micro Reaction Wheels,
Magnetic Torquers, single 1 N Hydrazine Thruster
Data Handling
S-band
Data Storage
16 Gb Solid State Recorder

        CARTOSAT – 2A:

CARTOSAT – 2A is the thirteenth satellite in the Indian Remote Sensing Satellite series (IRS). It is a sophisticated and rugged remote sensing satellite that can provide scene specific spot imagery. This satellite carries a Panchromatic Camera (PAN). The spatial resolution of this camera is better than 1m and swath of 9.6 km. Imageries from this satellite are used for cartographic applications like mapping, urban and rural infrastructure development and management, as well as application in Land Information (LIS) and Geographical Information System (GIS).




Mission
Remote Sensing
Weight
690 Kg (Mass at lift off)
Onboard Power
900 Watts
Stabilization
3 – axis body stabilised using high torque reaction wheels, magnetic torquers and hydrogen thrusters
Payloads
Panchromatic Camera
Launch date
28 April 2008
Launch site
SHAR Centre Sriharikota India
Launch vehicle
PSLV- C9
Orbit
635 kms, Polar Sun Synchronous
Inclination
97.94 deg
Mission life
5 years

CARTOSAT – 2:

Mission
Remote Sensing
Weight
650 Kg
Onboard Orbit
900 Watts
Stabilization
3 - axis body stabilised using high torque reaction wheels, magnetic torquers and thrusters
Payloads
Panchromatic Camera
Launch date
10 January 2007
Launch site
SHAR Centre Sriharikota India
Launch vehicle
PSLV- C7
Orbit
Polar Sun Synchronous
Mission life
5 years


CARTOSAT – 1:

CARTOSAT – 1 is the first Indian Remote Sensing Satellite capable of providing in-orbit stereo images. The images are used for Cartographic applications meeting the global requirements. Cameras of this satellite have a resolution of 2.5m (can distinguish a small car).

The Cartosat – 1 provides stereo pairs required for generating Digital Elevation Models, Ortho Image products, and Value added products for various applications of Geographical Information System (GIS).


Launch date
5 May 2005
Launch site
SHAR Centre Sriharikota India
Launch vehicle
PSLV- C6
Orbit
618 km Polar Sun Synchronous
Payloads
PAN FORE, PAN - AFT
Orbit Period
97 min
Number of Orbits Per day
14
Local time of equator crossing
10:30 am
Repetivity
126 days
Revisit
5 days
Lift-Off mass
1560 kg
Attitude and orbit control
3-axis body stabillised using reaction wheels, Magnetic Torquers and Hydrazine Thrusters
Electrical power
15 sqm Solar Array generating 1100w,
Two 24 Ah Ni-Cd batteries
Mission life
5 years

IRS P6/RESOURCESAT-1:

RESOURCESAT-1 is the tenth satellite of ISRO in IRS series, intended to not only continue the remote sensing data services provided by IRS-1C and IRS-1D, both of which have far outlived their designed mission lives, but also to vastly enhance the data quality. RESOURCESAT-1 is the most advanced Remote Sensing Satellite built by ISRO as of 2003.


Launch date
October 17, 2003
Launch site
SHAR, Sriharikota
Launch vehicle
PSLV-C5
Payloads
LISS-4, LISS-3, AWiFS-A, AWiFS-B
Orbit
Polar Sun Synchronous
Orbit height
817 km
Orbit inclination
98.7
Orbit period
101.35 min
Number of Orbits Per day
14
Local time of equator crossing
10:30 am
Repetivity (LISS-3)
24 days
Revisit
5 days
Lift-Off mass
1360 kg
Attitude and orbit control
3-axis body stabilised using Reaction Wheels, Magnetic Torquers and Hydrazine Thrusters
Power
Solar Array generating 1250 W, Two 24 Ah Ni-Cd batteries
Mission Life
5 years

Technology Experiment Satellite

The Technology Experiment Satellite (TES), weighing 1108 kg, was launched on October 22,2001. TES is an experimental satellite to demonstrate and validate the technologies like attitude and orbit control system, high-torque reaction wheels, new reaction control system, light-weight spacecraft structure, solid state recorder, X-band phased array antenna, improved satellite positioning system, miniaturised TTC and power systems and, two-mirror-on-axis camera optics.

TES also carried a panchromatic camera for remote sensing experiments.


Launch date
22 October 2001
Launch site
SHAR Centre Sriharikota India
Launch vehicle
PSLV- C3
Orbit
572 kms Sun Synchronous
Payloads
PAN

IRS-P4 (OCEANSAT):

IRS-P4 (OCEANSAT) is the first satellite primarily built for Ocean applications, weighing 1050 kg placed in a Polar Sun Synchronous orbit of 720 km, launched by PSLV-C2 from SHAR Centre, Sriharikota on May 26, 1999.

This satellite carries Ocean Colour Monitor (OCM) and a Multi - frequency Scanning Microwave Radiometer (MSMR) for oceanographic studies. IRS-P4 thus vastly augment the IRS satellite system of ISRO comprising four satellites, IRS-1B, IRS-1C, IRS-P3 and IRS-1D and extend remote sensing applications to several newer areas.

Mission completed on August 8, 2010 after serving for 11 years and 2 months.


Launch date
May 26, 1999
Launch site
SHAR, Sriharikota
Launch vehicle
PSLV - C2
Orbit
Polar Sun Synchronous
Altitude
720 km
Inclination
98.28 deg
Period
99.31 min
Local time of Eq. crossing
12 noon
Repetitivity cycle
2 days
Size
2.8m x 1.98m x 2.57m
Mass at lift off
1050 kg
Length when fully deployed
11.67 m
Attitude and Orbit Control
3-axis body-stabilised using Reaction Wheels, Magnetic Torquers and Hydrazine Thrusters
Power
9.6 Sq.m Solar Array generating 750w Two 21 Ah Ni-Cd Battries
Mission Completed On
August 8, 2010


IRS – 1D:

IRS – 1D was launched on September 27, 1997 by PSLV – C1. IRS – 1D, a follow on satellite to IRS – 1C belongs to the second generation of IRS series of Satellites. It has 3 payloads viz., PAN, LISS 3 & WiFS.

It has similar capabilities as IRC – 1C in terms of spatial resolution, spectral bands, stereoscopic imaging, wide field coverage and revisit capability. The improvements carried out in the IRS – 1D satellite taking into account the
IRS – 1C experiences have resulted in better quality imageries.

Mission completed during January 2010 after serving for 12 years and 3 months.


Mission
Operational Remote Sensing
Weight
1250kg
onboard power
809 Watts (generated by 9.6 sq.metres
Solar Panels)
Communication
S-band, X-band
Stabilization
Three axis body stabilized (zero momentum) with 4 Reaction Wheels, Magnetic torquer
RCS
Monopropellant Hydrazine based with sixteen
1 Newton thrusters & one 11 N thrusters
Payload
Three solid state Push Broom Cameras:
PAN (6 metre solution )
LlSS-3 (23.6 metre resolution) and
WiFS (189 metre resolution)
Onboard tape recorder
Storage Capacity : 62 G bits
Launch date
27 September 1997
Launch site
SHAR Centre Sriharikota India
Launch vehicle
PSLV-C1
Orbit (nomial)
817 km Polar Sun-synchronous
Achieved orbit
740 x 817 km
Inclination
98.6 
Local time
10.30 a.m. (descending node)
Mission completed on
January 2010

IRS-P3:

IRS-P3 was launched by PSLV-D3 on March 21, 1996 from SHAR Centre, Sriharikota, India. IRS-P3 carries two remote sensing payloads - Wide Field Sensor (WiFS) similar to that of IRS-1C, with an additional Short Wave Infrared Band (SWIR) and a Modular Opto-electronic Scanner (MOS). It also carries an X-ray astronomy payload and a C-band transponder for radar calibration.

Mission completed during January 2006 after serving 9 years and 10 months. 

Mission
Remote sensing of earth's natural resources. Study of X-ray Astronomy. Periodic calibration of PSLV tracking radar located at tracking stations.
Weight
920 kg
onboard power
817 Watts
Communication
S-band
Stabilization
Three axis body stabilized
RCS
Combinations of bladder type and surface tension type mass expulsion monopropellant hydrazine system
Payload
WideField Sensor (WiFS), Modular Opto - electronic Scanner (MOS),
Indian X-ray Astronomy Experiment (IXAE),
C-band transponder(CBT)
Launch date
March 21, 1996
Launch site
SHAR Centre, Sriharikota, India
Launch vehicle
PSLV-D3
Orbit
817 km. Circular polar sun-synchronous with
equatorial crossing at 10.30 am (descending node)
Inclination
98.68
Repetivity
WiFS : 5 days
Mission completed during
January 2006

IRS-1C:

IRS-1C is India's second generation operational Remote Sensing Satellite. The satellite carries Payloads with enhanced capabilities like better Spatial resolution additional spectral band, improved repeitivity and augment the Remote Sensing capability of the existing IRS-1A and IRS-1B.

Mission completed on September 21, 2007 after serving for 11 years and 8 months. 


Mission
Operational Remote Sensing
Weight
1250 kg
onboard power
809 Watts (generated by 9.6 sq.metres
Solar Panels)
Communication
S-band, X-band
Stabilization
Three axis body stabilized (zero momentum) with
4 Reaction Wheels, Magnetic torquer
RCS
Monopropellant Hydrazine based with sixteen
1 N thrusters & one 11N thrusters
Payload
Three solid state Push Broom Cameras:
PAN (<6 metre solution )LlSS-3(23.6 metre
resolution) and WiFS (189 metre resolution)
Onboard tape recorder
Storage Capacity : 62 G bits
Launch date
December 28, 1995
Launch site
Baikanur Cosmodrome Kazakhstan
Launch vehicle
Molniya
Orbit
817 km Polar Sun-synchronous
Inclination
98.69
Repetivity
24 days
Local time
10.30 a.m
Mission completed on
September 21, 2007

IRS-P2:

First Spacecraft successfully orbited onboard the second developmental flight of PSLV.

Mission completed during 1997 after serving for 3 years. 

Mission
Operational Remote Sensing
Weight
804 kg
onboard power
510 Watts
Communication
S-band, X-band
Stabilization
Three axis body stabilized with 4 Reaction Wheels,
Magnetic torquers
RCS
4 tanks containing Monopropellant Hydrazine
based with sixteen 1 N thrusters and one 11 N
thruster
Payload
Two solid state Push Broom Cameras operating in
four spectral bands in the visible and near-IR range
using CCD arrays: LlSS-2A & LlSS-2B
(Resolution: 32.74 metre)
Launch date
October 15, 1994
Launch site
SHAR Centre, Sriharikota, India
Launch vehicle
PSLV-D2
Inclination
98.68
Repetivity
24 days
Mission completed on
1997

IRS-1E:

IRS-1E satellite, derived from the engineering model of IRS-1A incorporating a Monocular Electro-Optical Stereo Scanner developed by DLR, Germany, and a LISS-I camera similar to that on IRS-1A, could not be placed into orbit by the PSLV-D1 launched in September 1993.

The mission was not realised due to problems faced by Launch Vehicle. It was the first development flight of PSLV.

Mission
Operational Remote Sensing
Weight
846 kg
onboard power
415 Watts
Communication
S-band (TIC) & VHF
Stabilization
Three axis body stabilized ( zero momentum) with 4 Reaction Wheels, Magnetic torquers
RCS
Monopropellant Hydrazine based RCS with 1 Newton thrusters ( 16 Nos.)
Payload
LlSS-1
MEOSS (Mono-ocula Erlectro Optic Stereo Scanner)
Launch date
September 20, 1993
Launch site
SHAR Centre, Sriharikota, India
Launch vehicle
PSLV-D1
Orbit
Not realized


IRS-1B:



Improved features compared to its predecessor  gyro referencing for better orientation sensing , time tagged commanding (IRS-1A) facility for more flexibility in camera operation and line count information for better data product generation.

Mission completed on December 20, 2003 after serving for 12 years and 4 months. 

Mission
Operational Remote Sensing
Weight
975 kg
Onboard power
600 Watts
Communication
S-band, X-band and VHF (commanding only)
Stabilization
Three axis body stabilized (zero momentum) with
4 Reactions Wheels, Magnetic torquers
RCS
Monopropellant Hydrazine based with sixteen
1 Newton thrusters
Payload
Three solid state Push Broom Cameras LlSS-1
(72.5 metre resolution), LlSS-2A and
LlSS-2B (36.25 metre resolution)
Launch date
August 29, 1991
Launch site
Baikanur Cosmodrome Kazakhstan
Launch vehicle
Vostok
Orbit
904 km Polar Sun Synchronous
Inclination
99.08
Repetivity
22 days
Local time
10.30 a.m. (descending node)
Mission Completed On
December 20, 2003

SROSS-2:
The satellite was launch onboard into second developmental site of ASLV. However did not reach the orbit.

Mission
Experimental
Weight
150 kg
Onboard power
90 Watts
Communication
S-band and VHF
Stabilization
Three axis body stabilized (biased momentum) with a Momentum Wheel and Magnetic Torquer
Propulsion system
Monopropellant (Hydrazine based)
Reaction Control System
Payload
Gamma Ray Burst (GRB) payload and Mono Payload
Ocular Electro-Optic Stereo Scanner (MEOSS) built by DLR, Germany
Launch date
July 13, 1988
Launch site
SHAR Centre, Sriharikota, India
Launch vehicle
Augmented Satellite Launch Vehicle (ASLV)
Orbit
Not realised

IRS-1A:

IRS-1A, the first of the series of indigenous state-of-art remote sensing satellites, was successfully launched into a polar sun-synchronous orbit on March 17, 1988 from the Soviet Cosmodrome at Baikonur. IRS-1A carries two cameras, LISS-I and LISS-II with resolutions of 73 metres and 36.25 metres respectively with a swath width of about 140 km during each pass over the country.

Mission completed during July 1996 after serving for 8 years and 4 months. 

Mission
Operational Remote Sensing
Weight
975 kg
Onboard power
600 Watts
Communication
S-band, X-band and VHF(commanding only)
Stabilization
Three axis body stabilized (zero momentum)
with 4 Reactions Wheels, Magnetic torquers
RCS
Monopropellant Hydrazine based with sixteen
1 Newton thrusters
Payload
Three solid state Push Broom Cameras:
LISS-1(72.5 metre resolution),
LISS-2A and
LISS-2B (36.25 metre resolution)
Launch date
March 17, 1988
Launch site
Baikanur Cosmodrome Kazakhstan
Launch vehicle
Vostok
Orbit
904 km Polar Sun-synchronous
Inclination
99.08
Repetivity
22 days (307 orbits)
Local time
10.30 a.m. (descending node)
Mission completed during
July 1996

RS-D2:
The satellite transmitted more than 5000 images and provided data on feature classification.

Mission
Experimental
Weight
41.5 kg
Onboard power
16 Watts
Communication
VHF band
Stabilization
Spin stabilized
Payload
Smart sensor (remote sensing payload),
L-bandbeacon
Launch date
April 17, 1983
Launch site
SHAR Centre, Sriharikota, India
Launch vehicle
SLV-3
Orbit
371 x 861 km
Inclination
46
Mission life
17 months
Orbital life
Seven years (Re-entered on April 19, 1990)


Bhaskara-II:

improved payload compared to Bhaskara-1.

Successful operation during mission life. Despite the problem faced by one of the two onboard cameras, sent more than two thousand images which were used for many studies. 

Mission
Experimental Remote Sensing
Weight
444 kg
onboard power
47 Watts
Communication
VHF band
Stabilization
Spin stabilized (spin axis controlled)
Payload
TV cameras, three band Microwave Radiometer (SAMIR)
Launch date
Nov 20, 1981
Launch site
Volgograd Launch Station (presently in Russia)
Launch vehicle
C-1 Intercosmos
Orbit
541 x 557 km
Inclination
50.7
Mission life
One year (nominal)
Orbital Life
About 10 years ( Re-entered in 1991 )

RS-D1:
Mission
Experimental
Weight
38 kg
onboard power
16 Watts
Communication
VHF band
Stabilization
Spin stabilized
Payload
Landmark Tracker ( remote sensing payload)
Launch date
May 31,1981
Launch site
SHAR Centre, Sriharikota, India
Launch vehicle
SLV-3
Orbit
186 x 418 km (achieved)
Inclination
46 deg
Orbital life
Nine days

BHASKAR-1:
The First Experimental Remote Sensing Satellite built in India.

The onboard TV camera sent imageries which we reused in the field of Hydrology and Forestry. SAMIR sent rich scientific data which were used for oceanographic studies. 

Mission
Experimental Remote Sensing
Weight
442 kg
onboard power
47 Watts
Communication
VHF band
Stabilization
Spin stabilized (spin axis controlled)
Payload
TVcameras, three band Microwave Radiometer (SAMIR)
Launch date
Jun 07,1979
Launch site
Volgograd Launch Station (presently in Russia)
Launch vehicle
C-1Intercosmos
Orbit
519 x 541 km
Inclination
50.6 deg
Mission life
One year (nominal)
Orbital Life
About 10 years ( Re-entered in 1989 )


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