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SROSS

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SROSS 3 Credit: Manufacturer Image

AKA: Stretched ROhini Satellite Series. Status: Operational 1987. First Launch: 1987-03-24. Last Launch: 1994-05-04. Number: 4 . Gross mass: 130 kg (280 lb). Height: 1.10 m (3.60 ft).

The Indian Space Research Organization (ISRO) developed the SROSS (Stretched Rohini Satellite Serie) spacecraft as follow-ons to the successful Rohini satellite series. The SROSS vehicles were designed to carry small scientific and technology payloads, including astrophysics, Earth remote sensing, and upper atmospheric monitoring experiments.

The vehicles were launched aboard developmental flights of India's new ASLV launcher. SROSS 1, intended primarily to monitor launch vehicle performance, was lost when the first flight of the ASLV ended in failure. SROSS 2 was destroyed in the loss of the second ASLV flight a year later. The third vehicle, SROSS C, was successfully placed into space, albeit in a much lower than planned orbit. The vehicle decayed on 14 July 1992, and although it returned some scientific data, was deemed only a partial success due to its much earlier than planned re-entry. SROSS C2 was the first unqualified success of the SROSS and ASLV programs.

The spacecraft was spin-stabilized with an octagonal structure. Body mounted and deployable solar panels provided ~100W (SROSS C2 had only body mounted panels) and recharged a NiCd battery. The payload capacity was 15-35 kg. SROSS 1 carried two retro-reflectors for laser tracking. SROSS 2 carried two instruments; a West German Monocular Electro Optical Stereo Scanner (MEOSS) and ISRO's 20-3000keV Gamma-ray Burst Experiment (GRB). SROSS C and C2 carried a gamma-ray burst (GRB) experiment and a Retarded Potential Analyzer (RPA) experiment. The GRB monitored celestial gamma ray bursts in the energy range 20-3000 keV. The RPA measured temperature, density and characteristics of electrons in the Earth's ionosphere.

Photo Gallery

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SROSS A Credit: Manufacturer Image

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SROSS B Credit: Manufacturer Image

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• 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).

• 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).

• 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.

• 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.