ASLV

All-solid orbital launch vehicle. Country: India. Status: Retired 1994. Other Designations: Advanced Satellite Launch Vehicle.

Manufacturer: ISRO. Launches: 4. Failures: 3. Success Rate: 25.00%. First Launch Date: 1987-03-24. Last Launch Date: 1994-05-04. Launch data is: complete. LEO Payload: 150 kg (330 lb). to: 400 km Orbit. Apogee: 900 km (550 mi). Associated Spacecraft: SROSS. Liftoff Thrust: 909.900 kN (204,554 lbf). Total Mass: 41,000 kg (90,000 lb). Core Diameter: 1.00 m (3.20 ft). Total Length: 23.50 m (77.00 ft). Flyaway Unit Cost $: 9.000 million. in: 1985 unit dollars.

• Stage0: 2 x ASLV-0. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 2,963 kg (6,532 lb). Motor: 1 x SLV-1. Thrust (vac): 502.600 kN (112,989 lbf). Isp: 253 sec. Burn time: 49 sec. Length: 9.99 m (32.77 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.

• Stage1: 1 x ASLV-1. Gross Mass: 11,800 kg (26,000 lb). Empty Mass: 2,900 kg (6,300 lb). Motor: 1 x SLV-1. Thrust (vac): 702.009 kN (157,818 lbf). Isp: 259 sec. Burn time: 45 sec. Length: 9.99 m (32.77 ft). Diameter: 1.00 m (3.20 ft). Propellants: Solid.

• Stage2: 1 x ASLV-2. Gross Mass: 4,400 kg (9,700 lb). Empty Mass: 800 kg (1,760 lb). Motor: 1 x SLV-2. Thrust (vac): 304.000 kN (68,341 lbf). Isp: 276 sec. Burn time: 36 sec. Length: 6.35 m (20.83 ft). Diameter: 0.80 m (2.62 ft). Propellants: Solid.

• Stage3: 1 x ASLV-3. Gross Mass: 1,710 kg (3,760 lb). Empty Mass: 650 kg (1,430 lb). Motor: 1 x SLV-3. Thrust (vac): 90.701 kN (20,390 lbf). Isp: 277 sec. Burn time: 45 sec. Length: 2.44 m (8.00 ft). Diameter: 0.82 m (2.69 ft). Propellants: Solid.

• Stage4: 1 x ASLV-4. Gross Mass: 512 kg (1,128 lb). Empty Mass: 195 kg (429 lb). Motor: 1 x SLV-4. Thrust (vac): 34.999 kN (7,868 lbf). Isp: 281 sec. Burn time: 33 sec. Length: 1.40 m (4.50 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.

1987 March 24 - Sriharikota SLV. 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 - Sriharikota SLV. 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 - Sriharikota SLV. 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.

1994 May 4 - 00:00 GMT - Sriharikota SLV. ASLV ASLV-D4 SROSS-C2 Mass: 113 kg (249 lb). Spacecraft: SROSS. Agency: ISRO. Perigee: 437 km (271 mi). Apogee: 938 km (582 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.