Technology Experiment Satellite (TES)

Name:Technology Experiment Satellite (TES)

LaunchDate:22.10.2001

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

 

GSAT-1

Name:GSAT-1

LaunchDate:18.04.2001

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

Name:INSAT-3B

LaunchDate:22.03.2000

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

Oceansat(IRS-P4)

Name:Oceansat(IRS-P4) LaunchDate:26.05.1999   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

INSAT-2E

Name:INSAT-2E

LaunchDate:03.04.1999

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

Name: INSAT-2DT

LaunchDate: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.

IRS-1D

Name:IRS-1D

LaunchDate:29.09.1997

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 o
Local time	10.30 a.m. (descending node)
Mission completed on	January 2010

INSAT-2D

Name:INSAT-2D

LaunchDate:04.06.1997

 

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 N24) With sixteen 22N thrusters and 440N LAM. 0
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

 

IRS-P3

Name:IRS-P3

LaunchDate:21.03.1996

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	98.68o
Repetivity	WiFS : 5 days
Mission completed during	January 2006

IRS-1C

Name:IRS-1C

LaunchDate:28.12.1995

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	98.69o
Repetivity	24 days
Local time	10.30 a.m
Mission completed on	September 21, 2007

INSAT-2C

Name:INSAT-2C

LaunchDate:07.12.1995

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 N24) With sixteen 22N thrusters and 440N LAM. 0
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

IRS-P2

Name:IRS-P2

LaunchDate:15.10.1994

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	98.68o
Respetivity	24 days
Mission completed on	1997

Stretched Rohini Satellite Series (SROSS-C2)

 

Name:Stretched Rohini Satellite Series (SROSS-C2) 

LaunchDate:04.05.1994

 

Second satellite successfully orbited by ASLV. Worked for four years after its launch.

 

Mission	Experimental
Weight	115 kg
Onboard power	45 Watts
Communication	S-band and VHF
RCS	Monopropellant Hydrazine based with six 1 Newton thrusters
Payload	Gamma Ray Burst (GRB) & Retarding Potential Analyser (RPA)
Launch date	May 04,1994
Launch site	SHAR Centre,Sriharikota,India
Launch vehicle	Augmented Satellite Launch Vehicle (ASLV)
Orbit	430 x 600 km.
Inclination	45 deg.
Mission life	Six months (nominal)
Orbital life	Two years (nominal)

IRS-1E

Name:IRS-1E

LaunchDate:20.09.1993

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 realised

INSAT-2B

Name:INSAT-2B

LaunchDate:23.07.1993

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 N24) With sixteen 22 N thrusters and 440 N LAM. 0
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