1993 September 20 - 05:12 GMT - Launch Vehicle: PSLV. PSLV-D1 FAILURE: Software error caused vehicle to go off course. IRS-1E Spacecraft: IRS. Agency: ISRO.

1994 October 15 - 05:05 GMT - Launch Vehicle: PSLV. PSLV-D2 IRS-P2 Mass: 870 kg (1,910 lb). Spacecraft: IRS. Agency: ISRO. Perigee: 818 km (508 mi). Apogee: 820 km (500 mi). Inclination: 98.67 deg. Period: 101.29 min. Remote sensing; sun-synch orbit.

1996 March 21 - 04:53 GMT - Launch Vehicle: PSLV. PSLV-D3 IRS-P3 Mass: 930 kg (2,050 lb). Spacecraft: IRS. Agency: ISRO. Perigee: 819 km (508 mi). Apogee: 820 km (500 mi). Inclination: 98.50 deg. Period: 101.30 min. LEO

1997 September 29 - 04:47 GMT - Launch Vehicle: PSLV. PSLV-C1 IRS-1D Spacecraft: IRS. Agency: ISRO. Perigee: 742 km (461 mi). Apogee: 823 km (511 mi). Inclination: 98.50 deg. Period: 100.50 min.

1999 May 26 - 06:22 GMT - Launch Vehicle: PSLV. PSLV-C2 Kitsat-3 Spacecraft: Kitsat. Agency: KAIST. Perigee: 716 km (444 mi). Apogee: 738 km (458 mi). Inclination: 98.40 deg.

2001 April 18 - 10:13 GMT - Launch Vehicle: GSLV. GSLV-D1 GSAT-1 Mass: 1,530 kg (3,370 lb). Spacecraft: Gsat. Agency: ISRO. Perigee: 33,825 km (21,017 mi). Apogee: 35,814 km (22,253 mi). Inclination: 0.00 deg. Period: 1,387.00 min. Experimental Rural Communications satellite. Launch delayed following pad abort on March 28. First launch of the Indian GSLV launch vehicle. GSat 1 was an Indian, 1500 kg scaled-dow) test model of a future geosynchronous communications spacecraft with a 440 N ISRO liquid apogee motor, and S-band and C-band ommunications transponders, similar to the Insat-2 satellites. The motor for the cryogenic, hydrogen-oxygen upper stage had been purchased from Russia but the design had never flown in space before. The stage cut off without providing the required delta-V - preliminary analysis revealed a shortfall of 0.5% in the thrust. An attempt was made to reach a usable orbit using the station-keeping motor of the GSAT satellite itself. After a series of burns, GSat 1 ran out of propellant - 10 kg more fuel would have been required to reach a stationary orbit. In the end, the parameters of the drifting (about 13 deg/day) orbit were period 23 hours, apogee 35,665 km, perigee 33,806 km, and inclination 0.99 deg. The fully functional transponders and transmitters on board were deactivated on instructions of the International Telecommunications Union. As of 4 September 2001 located at 54.88 deg E drifting at 13.212 deg E per day. As of 2007 Mar 10 located at 50.16W drifting at 12.778E degrees per day.

2001 October 22 - 04:53 GMT - Launch Vehicle: PSLV. PSLV-C3 TES Mass: 1,108 kg (2,442 lb). Spacecraft: TES. Agency: ISRO (India). Perigee: 550 km (340 mi). Apogee: 579 km (359 mi). Inclination: 97.80 deg. Launch delayed from July 20. The PS4 upper stage deployed the 1108 kg Indian TES (Technology Experiment Satellite) into a sun-synchronous orbit at 05:09:10 GMT. TES was an imaging satellite equipped with cameras and instruments to test military reconnaissance satellite technology. It was probably based on the IRS remote sensing satellite and carried a one-meter resolution panchromatic camera. India decided to develop an independent indigenous reconnaissance satellite capability after the 1999 incursion of Pakistani troops into disputed territory in Kashmir caught it by surprise. TES was developed by ISRO, the Indian Space Research Organization.

2002 September 12 - 10:25 GMT - Launch Vehicle: PSLV. PSLV-C4 METSAT Mass: 1,000 kg (2,200 lb). Spacecraft: Metsat. Agency: ISRO (India). Perigee: 35,764 km (22,222 mi). Apogee: 35,809 km (22,250 mi). Inclination: 0.30 deg. Period: 1,436.10 min. METSAT 1 was an Indian (ISRO) meteorological, geostationary satellite that was launched by an upgraded, four-stage PSLV-C4 rocket. The satellite was manoeuvred from the transfer orbit to a geostationary postion at 37° E longitude on September 16, and then was parked at 74° E longitude on September 24. As of 2007 Mar 11 located at 74.00E drifting at 0.007W degrees per day.

2003 May 8 - Launch Vehicle: GSLV. GSLV-D2 GSAT-2 Mass: 1,825 kg (4,023 lb). Spacecraft: Gsat. Agency: ISRO. Perigee: 35,782 km (22,233 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. Experimental Rural Communications. Launch delayed from original target of late 2001, then October 2002, then February 2003. The satellite carried 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 carried four piggyback experimental payloads: Total Radiation Dose Monitor (TRDM), Surface Charge Monitor (SCM), Solar X-ray Spectrometer (SOXS) and Coherent Radio Beacon Experiment (CRABEX). As of 2007 Mar 10 located at 47.97E drifting at 0.005E degrees per day.

2003 October 17 - 04:54 GMT - Launch Vehicle: PSLV. PSLV-C5 ResourceSat 1 (IRS-P6) Mass: 1,360 kg (2,990 lb). Spacecraft: IRS. Agency: Indian Space Research Organisation. Perigee: 813 km (505 mi). Apogee: 836 km (519 mi). Inclination: 98.80 deg. Period: 101.40 min. The satellite was to replace IRS-1C and IRS-1D, and carried three cameras for remote sensing, the highest resolution one being the 6-meter LISS-4 imager. The sensors were designed for agricultural remote sensing applications.

2004 September 20 - 10:31 GMT - Launch Vehicle: GSLV. GSLV-F01 GSAT-3 / Edusat Mass: 1,950 kg (4,290 lb). Spacecraft: Gsat. Agency: ISRO. Perigee: 35,772 km (22,227 mi). Apogee: 35,801 km (22,245 mi). Inclination: 0.10 deg. Period: 1,436.10 min. Gsat-3 / Edusat was the first Indian satellite built exclusively for the educational sector. It was mainly intended to meet the demand for an interactive satellite based distance education system for India. Edusat was launched into a geosynchronous transfer orbit by its launch vehicle. Edusat was to reach geostationary orbit by firing, in stages, its on board Liquid Apogee Motor (LAM). In geostationary orbit the satellite was to be co-located with Kalpana-1 and Insat-3C satellites at 74 deg East longitude.

Compared to earlier satellites in the Insat series, Edusat used several new technologies. The spacecraft was built around the I-2K standardised spacecraft bus. It had a multiple spot beam antenna with a 1.2 m reflector to direct Ku band spot beams, a dual core bent heat pipe for thermal control, high efficiency multi-junction solar cells and an improved thruster configuration for optimised propellant use for orbit and orientation maintenance. The satellite used radiatively cooled Ku-band Travelling Wave Tube Amplifiers and a dielectrically loaded C-band demultiplexer for its communication payloads. Edusat carried five Ku-band transponders providing spot beams, one Ku-band transponder providing a national beam and six Extended C-band transponders with a national coverage beam. It was to join the Insat system that already provided more than 130 transponders in C-band, Extended C-band and Ku-band for a variety of telecommunication and television services.

First operational flight of launch vehicle. Launch delayed from July, August and September 10. Dry mass 820 kg. As of 2007 Mar 9 located at 73.92E drifting at 0.006W degrees per day.