Encyclopedia Astronautica
ASLV



aslvj.jpg
ASLV
ASLV - COSPAR 1992-028
Indian all-solid orbital launch vehicle.

LEO Payload: 150 kg (330 lb) to a 400 km orbit. Failures: 3. Success Rate: 25.00%. First Fail Date: 1987-03-24. Last Fail Date: 1992-05-20. Launch data is: complete in 1985 dollars. Flyaway Unit Cost $: 9.000 million.

Stage Data - ASLV

  • Stage 0. 2 x ASLV-0. Gross Mass: 11,600 kg (25,500 lb). Empty Mass: 2,963 kg (6,532 lb). Thrust (vac): 502.600 kN (112,989 lbf). Isp: 253 sec. Burn time: 49 sec. Isp(sl): 229 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 9.99 m (32.77 ft). Propellants: Solid. No Engines: 1. Engine: SLV-1. Other designations: Advanced Satellite Launch Vehicle. Status: In Production.
  • Stage 1. 1 x ASLV-1. Gross Mass: 11,800 kg (26,000 lb). Empty Mass: 2,900 kg (6,300 lb). Thrust (vac): 702.009 kN (157,818 lbf). Isp: 259 sec. Burn time: 45 sec. Isp(sl): 232 sec. Diameter: 1.00 m (3.20 ft). Span: 1.00 m (3.20 ft). Length: 9.99 m (32.77 ft). Propellants: Solid. No Engines: 1. Engine: SLV-1. Other designations: Advanced Satellite Launch Vehicle. Status: In Production.
  • Stage 2. 1 x ASLV-2. Gross Mass: 4,400 kg (9,700 lb). Empty Mass: 800 kg (1,760 lb). Thrust (vac): 304.000 kN (68,341 lbf). Isp: 276 sec. Burn time: 36 sec. Isp(sl): 220 sec. Diameter: 0.80 m (2.62 ft). Span: 0.80 m (2.62 ft). Length: 6.35 m (20.83 ft). Propellants: Solid. No Engines: 1. Engine: SLV-2. Other designations: Advanced Satellite Launch Vehicle. Status: In Production.
  • Stage 3. 1 x ASLV-3. Gross Mass: 1,710 kg (3,760 lb). Empty Mass: 650 kg (1,430 lb). Thrust (vac): 90.701 kN (20,390 lbf). Isp: 277 sec. Burn time: 45 sec. Isp(sl): 190 sec. Diameter: 0.82 m (2.69 ft). Span: 0.82 m (2.69 ft). Length: 2.44 m (8.00 ft). Propellants: Solid. No Engines: 1. Engine: SLV-3. Other designations: Advanced Satellite Launch Vehicle. Status: In Production.
  • Stage 4. 1 x ASLV-4. Gross Mass: 512 kg (1,128 lb). Empty Mass: 195 kg (429 lb). Thrust (vac): 34.999 kN (7,868 lbf). Isp: 281 sec. Burn time: 33 sec. Isp(sl): 110 sec. Diameter: 0.66 m (2.16 ft). Span: 0.66 m (2.16 ft). Length: 1.40 m (4.50 ft). Propellants: Solid. No Engines: 1. Engine: SLV-4. Other designations: Advanced Satellite Launch Vehicle. Status: In Production.

AKA: Advanced Satellite Launch Vehicle.
Status: Retired 1994.
Gross mass: 41,000 kg (90,000 lb).
Payload: 150 kg (330 lb).
Height: 23.50 m (77.00 ft).
Diameter: 1.00 m (3.20 ft).
Thrust: 909.90 kN (204,554 lbf).
Apogee: 400 km (240 mi).
First Launch: 1987.03.24.
Last Launch: 1994.05.04.
Number: 4 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • SROSS Indian earth magnetosphere satellite. 4 launches, 1987.03.24 (SROSS A) to 1994.05.04 (SROSS-C2). More...

Associated Engines
  • SLV-1 ISRO solid rocket engine. 502.6 kN. Isp=253s. Used on ASLV, PSLV, SLV. First flight 1979. More...
  • SLV-2 ISRO solid rocket engine. 267 kN. Isp=267s. Used on ASLV, SLV. First flight 1979. More...
  • SLV-3 ISRO solid rocket engine. 90.7 kN. Isp=277s. Used on ASLV, SLV. First flight 1979. More...
  • SLV-4 ISRO solid rocket engine. 26.8 kN. Isp=283s. Used on ASLV, SLV. First flight 1979. More...

See also
Associated Manufacturers and Agencies
  • ISRO Indian manufacturer of rockets, spacecraft, and rocket engines. Indian Space Research Organization, India. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.
  • Krebs, Gunter, Gunter's Space Page, University of Frankfurt, 1996. Web Address when accessed: here.
  • JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: here.
  • Isakowitz, Steven J,, International Reference to Space Launch Systems Second Edition, AIAA, Washington DC, 1991 (succeeded by 2000 edition).
  • Wilson, Andrew, editor,, Jane's/Interavia Space Directory, Jane's Information Group, Coulsdon, Surrey, 1992 et al.

Associated Launch Sites
  • Sriharikota India's primary space launch center, located on the east coast of the peninsula with a firing sector over the Bay of Bengal. In use from 1971 to present. More...

Associated Stages
  • ASLV-4 Solid propellant rocket stage. Loaded/empty mass 512/195 kg. Thrust 35.00 kN. Vacuum specific impulse 281 seconds. More...
  • ASLV-3 Solid propellant rocket stage. Loaded/empty mass 1,710/650 kg. Thrust 90.70 kN. Vacuum specific impulse 277 seconds. More...
  • ASLV-0 Solid propellant rocket stage. Loaded/empty mass 11,600/2,963 kg. Thrust 502.60 kN. Vacuum specific impulse 253 seconds. More...
  • ASLV-1 Solid propellant rocket stage. Loaded/empty mass 11,800/2,900 kg. Thrust 702.01 kN. Vacuum specific impulse 259 seconds. More...
  • ASLV-2 Solid propellant rocket stage. Loaded/empty mass 4,400/800 kg. Thrust 304.00 kN. Vacuum specific impulse 276 seconds. More...

ASLV Chronology


1987 March 24 - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. Launch Vehicle: ASLV. LV Configuration: ASLV ASLV-D1. 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 . COSPAR: F870324A. Apogee: 10 km (6 mi).

1988 July 13 - . 09:18 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. Launch Vehicle: ASLV. LV Configuration: ASLV ASLV-D2. 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 . COSPAR: F880712A. Apogee: 25 km (15 mi).

1992 May 20 - . 00:30 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. Launch Vehicle: ASLV. LV Configuration: ASLV ASLV-D3. 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: 46.0000 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. LV Configuration: ASLV ASLV-D4.
  • 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: 46.2000 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.

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