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SLV-3
All-solid orbital launch vehicle. Country: India. Status: Retired 1983. Other Designations: Satellite Launch Vehicle.

Manufacturer: ISRO. Launches: 4. Failures: 2. Success Rate: 50.00%. First Launch Date: 1979-08-10. Last Launch Date: 1983-04-17. Launch data is: complete. LEO Payload: 40 kg (88 lb). to: 400 km Orbit. Associated Spacecraft: Rohini, Rohini 1A, Rohini 2. Liftoff Thrust: 454.900 kN (102,266 lbf). Total Mass: 17,610 kg (38,820 lb). Core Diameter: 1.00 m (3.20 ft). Total Length: 24.00 m (78.00 ft). Flyaway Unit Cost $: 5.000 million. in: 1985 unit dollars. Version:

SLV-3.

Four stage vehicle consisting of 1 x SLV-3-1 + 1 x SLV-3-2 + 1 x SLV-3-3 + 1 x SLV-3-4

Launches: 4. Failures: 2. First Launch Date: 1979-08-10. Last Launch Date: 1983-04-17. LEO Payload: 42 kg (92 lb). Apogee: 900 km (550 mi). Liftoff Thrust: 503.000 kN (113,078 lbf). Total Mass: 17,000 kg (37,000 lb). Core Diameter: 1.00 m (3.20 ft). Total Length: 23.60 m (77.40 ft).

  • Stage1: 1 x SLV-1. Gross Mass: 10,800 kg (23,800 lb). Empty Mass: 2,140 kg (4,710 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.
  • Stage2: 1 x SLV-2. Gross Mass: 4,900 kg (10,800 lb). Empty Mass: 1,750 kg (3,850 lb). Motor: 1 x SLV-2. Thrust (vac): 267.005 kN (60,025 lbf). Isp: 267 sec. Burn time: 40 sec. Length: 6.35 m (20.83 ft). Diameter: 0.80 m (2.62 ft). Propellants: Solid.
  • Stage3: 1 x SLV-3. Gross Mass: 1,500 kg (3,300 lb). Empty Mass: 440 kg (970 lb). Motor: 1 x SLV-3. Thrust (vac): 90.701 kN (20,390 lbf). Isp: 277 sec. Burn time: 45 sec. Length: 2.30 m (7.50 ft). Diameter: 0.82 m (2.69 ft). Propellants: Solid.
  • Stage4: 1 x SLV-4. Gross Mass: 360 kg (790 lb). Empty Mass: 98 kg (216 lb). Motor: 1 x SLV-4. Thrust (vac): 26.830 kN (6,032 lbf). Isp: 283 sec. Burn time: 33 sec. Length: 1.50 m (4.90 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.
Version:

SLV-3 D4.

Four stage vehicle consisting of 1 x SLV-3-1 + 1 x SLV-3-2 + 1 x SLV-3-3 + 1 x AS-4

LEO Payload: 42 kg (92 lb).

  • Stage1: 1 x SLV-1. Gross Mass: 10,800 kg (23,800 lb). Empty Mass: 2,140 kg (4,710 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.
  • Stage2: 1 x SLV-2. Gross Mass: 4,900 kg (10,800 lb). Empty Mass: 1,750 kg (3,850 lb). Motor: 1 x SLV-2. Thrust (vac): 267.005 kN (60,025 lbf). Isp: 267 sec. Burn time: 40 sec. Length: 6.35 m (20.83 ft). Diameter: 0.80 m (2.62 ft). Propellants: Solid.
  • Stage3: 1 x SLV-3. Gross Mass: 1,500 kg (3,300 lb). Empty Mass: 440 kg (970 lb). Motor: 1 x SLV-3. Thrust (vac): 90.701 kN (20,390 lbf). Isp: 277 sec. Burn time: 45 sec. Length: 2.30 m (7.50 ft). Diameter: 0.82 m (2.69 ft). Propellants: Solid.
  • Stage4: 1 x SLV-4. Gross Mass: 360 kg (790 lb). Empty Mass: 98 kg (216 lb). Motor: 1 x SLV-4. Thrust (vac): 26.830 kN (6,032 lbf). Isp: 283 sec. Burn time: 33 sec. Length: 1.50 m (4.90 ft). Diameter: 0.66 m (2.16 ft). Propellants: Solid.
SLV Chronology

1979 August 10 - Sriharikota SLV. SLV-3 SLV-3-E1 FAILURE: Thrust vectoring of second stage failed. Rohini 1A Spacecraft: Rohini 1A. Agency: ISRO.

1980 July 18 - 02:33 GMT - Sriharikota SLV. SLV-3 SLV-3-E2 Rohini RS-1 Mass: 40 kg (88 lb). Spacecraft: Rohini. Agency: ISRO. Perigee: 307 km (190 mi). Apogee: 921 km (572 mi). Inclination: 44.70 deg. Period: 97.00 min. Experimental-technology mission. Rohini satellite RS-1.

1981 May 31 - 05:00 GMT - Sriharikota SLV. SLV-3 SLV-3-D3 FAILURE: Partial Failure. Rohini 2 Spacecraft: Rohini 2. Agency: ISRO. Perigee: 181 km (112 mi). Apogee: 374 km (232 mi). Inclination: 46.20 deg. Period: 90.06 min. Orbit too low.

1983 April 17 - 05:44 GMT - Sriharikota SLV. SLV-3-D4 SLV-3-D4 Rohini 3 Mass: 42 kg (92 lb). Spacecraft: Rohini. Agency: ISRO. Perigee: 326 km (202 mi). Apogee: 485 km (301 mi). Inclination: 46.60 deg. Period: 92.70 min. Rohini satellite D-2. Second developmental flight of an SLV-3 launch vehicle. The Rohini satellite D-2 carried a sensor payload for conducting remote-sensing experiments and for accurate orbit and attitude determination.

Bibliography:

  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: http://www.planet4589.org/jsr.html.
  • Krebs, Gunter, Gunter's Space Page, University of Frankfurt, 1996. Web Address when accessed: http://www.skyrocket.de/space.
  • JPL Mission and Spacecraft Library, Jet Propulsion Laboratory, 1997. Web Address when accessed: http://msl.jpl.nasa.gov/home.html.
  • 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.
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