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 )

Space Mission

Indian space programme encompasses research in areas like astronomy, astrophysics, planetary and earth sciences, atmospheric sciences and theoretical physics. Balloons, sounding rockets, space platforms and ground-based facilities support these research efforts. A series of sounding rockets are available for atmospheric experiments. Several scientific instruments have been flown on satellites especially to direct celestial X-ray and gamma-ray bursts.Major space missions are Chandrayaan-l and forthcoming Megha - Tropiques.

Chandrayaan-l

Chandrayaan-1, India's first mission to Moon, was launched successfully on October 22, 2008 from SDSC SHAR, Sriharikota. The spacecraft was orbiting around the Moon at a height of 100 km from the lunar surface for chemical, mineralogical and photo-geologic mapping of the Moon. The spacecraft carries 11 scientific instruments built in India, USA, UK, Germany, Sweden and Bulgaria.After the successful completion of all the major mission objectives, the orbit has been raised to 200 km during May 2009.  Mission Remote Sensing, Planetary Science Weight 1380 kg (Mass at lift off) Onboard power 700 Watts Stabilization 3 - axis stabilised using reaction wheel and attitude control thrusters, sun sensors, star sensors, fibre optic gyros and accelerometers for attitude determination. Payloads Scientific Payloads from India a) Terrain Mapping Camera (TMC) b) Hyper Spectral Imager (HySI) c) Lunar Laser Ranging Instrument (LLRI) d) High Energy X - ray Spectrometer (HEX) e) Moon Impact Probe(MIP) Scientific Payloads from abroad f) Chandrayaan-I  X-ray Spectrometer (CIXS) g) Near Infrared Spectrometer (SIR - 2) h) Sub keV Atom Reflecting Analyzer (SARA) i) Miniature Synthetic Aperature Radar (Mini SAR) j) Moon Mineralogy Mapper (M3) k) Radiation Dose Monitor (RADOM) Launch Date 22 October 2008 Launch Site SDSC, SHAR, Sriharikota Launch Vehicle PSLV - C11 Orbit 100 km x 100 km : Lunar Orbit Mission life 2 years SROSS-C2 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) SROSS-C First satellite successfully orbited by ASLV Mission Experimental Weight 106.1 kg Onboard power 45 Watts Communication S-band and VHF Stabilization Spin stabilized with a Magnetic Torquer and Magnetic Bias Control Payload Gamma Ray Burst (GRB) experiment & Retarding Potential Analyser (RPA) experiment Launch date May 20,1992 Launch site SHAR Centre,Sriharikota,India Launch vehicle Augmented Satellite Launch Vehicle (ASLV) Orbit 267 x 391 km Mission life Two months (Re-entered on July15,1992) SROSS-1 This satellite was launched onboard the first developmental a flight of ASLV. It 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 Launch Vehicle Monitoring Platform(LVMP), Gamma Ray Burst (GRB) payload and Corner Cube Retro Reflector (CCRR) for laser tracking Launch date March 24, 1987 Launch site SHAR Centre, Sriharikota, India Launch vehicle Augmented Satellite Launch Vehicle (ASLV) Orbital life Not realised