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.