ASLV - Augmented Satellite Launch vehicle - LEO Booster

Augmented SLV

ASLV was the springboard to the advanced Polar Satellite Launch Vehicle (PSLV). The ASLV was not a simple variant of the SLV-3 but a more complex vehicle. The ASLV is actually a 5-stage vehicle since the core first stage does not ignite until just before the 2 booster rockets burn out. The payload capacity of the ASLV is approximately 150 kg to an orbit of 400 km with a 47-degree inclination. Three successive failures plunged the project into a crisis. ISRO scientist had to confront new technological challenges and one of the important design changes was the addition of the 2 strap on boosters attached to either side of the first stage. Strap on separation, bulbous heat shield, "closed loop" guidance system as opposed to the "open loop" guidance system of the SLV-3 and heat shield management and separation had to be adapted by the scientists. However, all the problems and new technological challenges were overcome with ISRO's customary resolve and zeal, and the important ASLV program crossed an important rubicon.

ASLV Details

Launches: 4. 
Failures: 3. 
Success Rate: 25.00% pct. 
First Launch Date: 24 March 1987. 
Last Launch Date: 04 May 1994. 
Payload: 150 kg. to: 400 km Orbit. 
Stages: 4
Liftoff Thrust: 92,780 kgf. Total Mass: 41,000 kg. 
Core Diameter: 1.0 m. 
Total Length: 23.5 m. 

Launch Updates

24 March 1987 on Launch Vehicle ASLV-D1 from Sriharikota. FAILURE: Second stage failed to ignite. Spacecraft: SROSS A. Mass: 150 kg. 
12 July 1988 on Launch Vehicle ASLV-D2 from Sriharikota. FAILURE: First stage failure. Insufficient control gain. Spacecraft: SROSS B. Mass: 150 kg. 
20 May 1992 on Launch Vehicle ASLV-D3 from Sriharikota. FAILURE: Insufficent spin stabilisation of fifth stage. Partial Failure. Spacecraft: SROSS C. Mass: 106 kg. 
4 May 1994 on Launch Vehicle ASLV-D4 from Sriharikota. Spacecraft: SROSS C-2. Mass: 113 kg.
SROSS - 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, consisting of two scintillators to study celestial gamma ray bursts in the energy range of 20 keV to 3000 keV.