Sriharikota SLV

1979 August 10

Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: SLV. Launch Vehicle: SLV-3. FAILURE: Thrust vectoring of second stage failed.. Failed Stage: 2.

• Rohini 1A - . Payload: Rohini RS-1. Nation: India. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Rohini 1A. Decay Date: 1979-08-19 .

1980 July 18

02:33 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: SLV. Launch Vehicle: SLV-3.

• Rohini RS-1 - . Payload: Rohini 1B. Mass: 40 kg (88 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: Rohini. Decay Date: 1981-05-20 . USAF Sat Cat: 11899 . COSPAR: 1980-062A. Apogee: 921 km (572 mi). Perigee: 307 km (190 mi). Inclination: 44.70 deg. Period: 97.00 min. Experimental-technology mission. Rohini satellite RS-1. .

1981 May 31

05:00 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: SLV. Launch Vehicle: SLV-3. FAILURE: Partial Failure.. Failed Stage: U.

• Rohini 2 - . Payload: Rohini RS-D-1. Nation: India. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Rohini 2. Decay Date: 1981-05-31 . USAF Sat Cat: 12491 . COSPAR: 1981-051A. Apogee: 374 km (232 mi). Perigee: 181 km (112 mi). Inclination: 46.20 deg. Period: 90.06 min. Orbit too low..

1983 April 17

05:44 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: SLV. Launch Vehicle: SLV-3.

• Rohini 3 - . Payload: Rohini RS-D-2. Mass: 42 kg (92 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: Rohini. Decay Date: 1990-04-19 . USAF Sat Cat: 14002 . COSPAR: 1983-033A. Apogee: 485 km (301 mi). Perigee: 326 km (202 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 Site: Sriharikota. Launch Complex: Sriharikota SLV. Launch Vehicle: ASLV. FAILURE: Second stage failed to ignite.. Failed Stage: 2.

• SROSS A - . Mass: 150 kg (330 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SROSS. Decay Date: 1987-03-24 . Apogee: 10 km (6 mi).

1988 July 13

09:18 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. Launch Vehicle: ASLV. FAILURE: First stage failure. Insufficient control gain.. Failed Stage: 1.

• SROSS B - . Mass: 150 kg (330 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SROSS. Decay Date: 1988-07-13 . Apogee: 25 km (15 mi).

1992 May 20

00:30 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. Launch Vehicle: ASLV. FAILURE: Insufficient spin stabilization of fifth stage. Partial Failure.. Failed Stage: 5.

• SROSS 3 - . Payload: SROSS C. Mass: 106 kg (233 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SROSS. Decay Date: 1992-07-14 . USAF Sat Cat: 21968 . COSPAR: 1992-028A. Apogee: 436 km (270 mi). Perigee: 251 km (155 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.

1994 May 4

00:00 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. Launch Vehicle: ASLV.

• SROSS-C2 - . Payload: SROSS C2. Mass: 113 kg (249 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SROSS. Decay Date: 2001-07-12 . USAF Sat Cat: 23099 . COSPAR: 1994-027A. Apogee: 938 km (582 mi). Perigee: 437 km (271 mi). Inclination: 46.20 deg. Period: 98.00 min.

  Streched Rohini Satellite Series; measured ionospheric plasma and gamma rays. SROSS-C2 satellite carries two scientific payloads: (i) Retarding Potential Analyser (RPA), consisting of two planar detectors to measure plasma parameters and investigate energetics of the equatorial ionosphere. (ii) Gamma Ray Burst (GRB) detectors, cons isting of two scintillators to study celestial gamma ray bursts in the energy range of 20 keV to 3000 keV. Launch vehicle Augmented Satellite Launch Vehicle ASLV-D4.