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Family: SLV. Country: India. Status: Hardware. Other Designations: Advanced Satellite Launch Vehicle.
SpecificationsLaunches: 4. Failures: 3. Success Rate: 25.00% pct. First Launch Date: 24 March 1987. Last Launch Date: 04 May 1994. LEO Payload: 150 kg. to: 400 km Orbit. Liftoff Thrust: 92,780 kgf. Total Mass: 41,000 kg. Core Diameter: 1.0 m. Total Length: 23.5 m. Flyaway Unit Cost $: 9.00 million. in 1985 unit dollars.
- Stage Number: 0. 2 x ASLV-0 Gross Mass: 11,600 kg. Empty Mass: 2,963 kg. Thrust (vac): 51,251 kgf. Isp: 253 sec. Burn time: 49 sec. Isp(sl): 229 sec. Diameter: 1.0 m. Span: 1.0 m. Length: 10.0 m. Propellants: Solid No Engines: 1. SLV-1
- Stage Number: 1. 1 x ASLV-1 Gross Mass: 11,800 kg. Empty Mass: 2,900 kg. Thrust (vac): 71,585 kgf. Isp: 259 sec. Burn time: 45 sec. Isp(sl): 232 sec. Diameter: 1.0 m. Span: 1.0 m. Length: 10.0 m. Propellants: Solid No Engines: 1. SLV-1
- Stage Number: 2. 1 x ASLV-2 Gross Mass: 4,400 kg. Empty Mass: 800 kg. Thrust (vac): 31,000 kgf. Isp: 276 sec. Burn time: 36 sec. Isp(sl): 220 sec. Diameter: 0.8 m. Span: 0.8 m. Length: 6.4 m. Propellants: Solid No Engines: 1. SLV-2
- Stage Number: 3. 1 x ASLV-3 Gross Mass: 1,710 kg. Empty Mass: 650 kg. Thrust (vac): 9,249 kgf. Isp: 277 sec. Burn time: 45 sec. Isp(sl): 190 sec. Diameter: 0.8 m. Span: 0.8 m. Length: 2.4 m. Propellants: Solid No Engines: 1. SLV-3
- Stage Number: 4. 1 x ASLV-4 Gross Mass: 512 kg. Empty Mass: 195 kg. Thrust (vac): 3,569 kgf. Isp: 281 sec. Burn time: 33 sec. Isp(sl): 110 sec. Diameter: 0.7 m. Span: 0.7 m. Length: 1.4 m. Propellants: Solid No Engines: 1. SLV-4
ASLV Chronology
1987 Mar 24 - LV Configuration: ASLV s/n ASLV-D1. Launch Site: Sriharikota . FAILURE: Second stage failed to ignite.
- SROSS A Spacecraft: SROSS. Mass: 150 kg.
1988 Jul 12 - LV Configuration: ASLV s/n ASLV-D2. Launch Site: Sriharikota . FAILURE: First stage failure. Insufficient control gain.
- SROSS B Spacecraft: SROSS. Mass: 150 kg.
1992 May 20 - - 00:30 GMT. LV Configuration: ASLV s/n ASLV-D3. Launch Site: Sriharikota . FAILURE: Insufficent spin stabilisation of fifth stage. Partial Failure.
- SROSS 3 Spacecraft: SROSS. Payload: SROSS C. Mass: 106 kg.
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. LV Configuration: ASLV s/n ASLV-D4. Launch Site: Sriharikota .
- SROSS-C2 Spacecraft: SROSS. Payload: SROSS C2. Mass: 113 kg.
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.
Bibliography:- 42 - Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991.
- 61 - Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.
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Last update 12 March 2001.
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