1979 August 10 - Launch Vehicle: SLV. SLV-3 SLV-3-E1 FAILURE: Thrust vectoring of second stage failed. Rohini 1A Spacecraft: Rohini 1A. Agency: ISRO.

1980 July 18 - 02:33 GMT - Launch Vehicle: SLV. SLV-3 SLV-3-E2 Rohini RS-1 Mass: 40 kg (88 lb). Spacecraft: Rohini. Agency: ISRO. Perigee: 307 km (190 mi). Apogee: 921 km (572 mi). Inclination: 44.70 deg. Period: 97.00 min. Experimental-technology mission. Rohini satellite RS-1.

1981 May 31 - 05:00 GMT - Launch Vehicle: SLV. SLV-3 SLV-3-D3 FAILURE: Partial Failure. Rohini 2 Spacecraft: Rohini 2. Agency: ISRO. Perigee: 181 km (112 mi). Apogee: 374 km (232 mi). Inclination: 46.20 deg. Period: 90.06 min. Orbit too low.

1983 April 17 - 05:44 GMT - Launch Vehicle: SLV. SLV-3-D4 SLV-3-D4 Rohini 3 Mass: 42 kg (92 lb). Spacecraft: Rohini. Agency: ISRO. Perigee: 326 km (202 mi). Apogee: 485 km (301 mi). Inclination: 46.60 deg. Period: 92.70 min. Rohini satellite D-2. Second developmental flight of an SLV-3 launch vehicle. The Rohini satellite D-2 carried a sensor payload for conducting remote-sensing experiments and for accurate orbit and attitude determination.

1987 March 24 - Launch Vehicle: ASLV. ASLV ASLV-D1 FAILURE: Second stage failed to ignite. SROSS A Mass: 150 kg (330 lb). Spacecraft: SROSS. Agency: ISRO. Apogee: 10 km (6 mi).

1988 July 13 - 09:18 GMT - Launch Vehicle: ASLV. ASLV ASLV-D2 FAILURE: First stage failure. Insufficient control gain. SROSS B Mass: 150 kg (330 lb). Spacecraft: SROSS. Agency: ISRO. Apogee: 25 km (15 mi).

1992 May 20 - 00:30 GMT - Launch Vehicle: ASLV. ASLV ASLV-D3 FAILURE: Insufficient spin stabilization of fifth stage. Partial Failure. SROSS 3 Mass: 106 kg (233 lb). Spacecraft: SROSS. Agency: ISRO. Perigee: 251 km (155 mi). Apogee: 436 km (270 mi). Inclination: 46.00 deg. Period: 91.40 min. Stretched Rohini Satellite Series; carried gamma-ray detector, ionosphere monitor. SROSS-C satellite carries two scientific payloads: 1) Retarding Potential Analyser (RPA), consisting of two planar detectors to measure plasma parameters and investigate energetics of the equatorial ionosphere. (2) Gamma Ray Burst (GRB) detectors, consist ing of two scintillation detectors to study celestial gamma ray bursts in the energy range of 20 keV to 3000 keV. Launch vehicle: Augmented Satellite Launch Vehicle.