SLV

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SLV
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SLV-3

Indian all-solid orbital launch vehicle.

AKA: Satellite Launch Vehicle. Status: Retired 1983. Payload: 40 kg (88 lb). Thrust: 454.90 kN (102,266 lbf). Gross mass: 17,610 kg (38,820 lb). Height: 24.00 m (78.00 ft). Diameter: 1.00 m (3.20 ft). Apogee: 400 km (240 mi).

LEO Payload: 40 kg (88 lb) to a 400 km orbit. Flyaway Unit Cost 1985$: 5.000 million.

Stage Data - SLV

Stage 1. 1 x SLV-1. Gross Mass: 10,800 kg (23,800 lb). Empty Mass: 2,140 kg (4,710 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: Satellite Launch Vehicle. Status: In Production.

Stage 2. 1 x SLV-2. Gross Mass: 4,900 kg (10,800 lb). Empty Mass: 1,750 kg (3,850 lb). Thrust (vac): 267.005 kN (60,025 lbf). Isp: 267 sec. Burn time: 40 sec. Isp(sl): 216 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: Satellite Launch Vehicle. Status: In Production.

Stage 3. 1 x SLV-3. Gross Mass: 1,500 kg (3,300 lb). Empty Mass: 440 kg (970 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: 2.30 m (7.50 ft). Propellants: Solid. No Engines: 1. Engine: SLV-3. Other designations: Satellite Launch Vehicle. Status: In Production.

Stage 4. 1 x SLV-4. Gross Mass: 360 kg (790 lb). Empty Mass: 98 kg (216 lb). Thrust (vac): 26.830 kN (6,032 lbf). Isp: 283 sec. Burn time: 33 sec. Isp(sl): 60 sec. Diameter: 0.66 m (2.16 ft). Span: 0.66 m (2.16 ft). Length: 1.50 m (4.90 ft). Propellants: Solid. No Engines: 1. Engine: SLV-4. Other designations: Satellite Launch Vehicle. Status: In Production.

More at: SLV.

Subtopics

SLV-3 Indian all-solid orbital launch vehicle. 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

SLV-3 D4 Indian all-solid orbital launch vehicle. Four stage vehicle consisting of 1 x SLV-3-1 + 1 x SLV-3-2 + 1 x SLV-3-3 + 1 x AS-4

Family: all-solid, orbital launch vehicle. Country: India. Spacecraft: Rohini 1A, Rohini, Rohini 2. Stages: SLV-3 engine, SLV-1, SLV-2, SLV-4. Agency: ISRO. Bibliography: 2, 42, 5, 6, 61.

1979 August 10 - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: SLV. Launch Vehicle: SLV-3. FAILURE: Thrust vectoring of second stage failed.. Failed Stage: 2.

Rohini 1A - . Payload: Rohini RS-1. Nation: India. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Rohini 1A. Decay Date: 1979-08-19 .

1980 July 18 - . 02:33 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: SLV. Launch Vehicle: SLV-3.

Rohini RS-1 - . Payload: Rohini 1B. Mass: 40 kg (88 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: Rohini. Decay Date: 1981-05-20 . USAF Sat Cat: 11899 . COSPAR: 1980-062A. Apogee: 921 km (572 mi). Perigee: 307 km (190 mi). Inclination: 44.70 deg. Period: 97.00 min. Experimental-technology mission. Rohini satellite RS-1. .

1981 May 31 - . 05:00 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: SLV. Launch Vehicle: SLV-3. FAILURE: Partial Failure.. Failed Stage: U.

Rohini 2 - . Payload: Rohini RS-D-1. Nation: India. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Rohini 2. Decay Date: 1981-05-31 . USAF Sat Cat: 12491 . COSPAR: 1981-051A. Apogee: 374 km (232 mi). Perigee: 181 km (112 mi). Inclination: 46.20 deg. Period: 90.06 min. Orbit too low..

1983 April 17 - . 05:44 GMT - . Launch Site: Sriharikota. Launch Complex: Sriharikota SLV. LV Family: SLV. Launch Vehicle: SLV-3.

Rohini 3 - . Payload: Rohini RS-D-2. Mass: 42 kg (92 lb). Nation: India. Agency: ISRO. Class: Earth. Type: Earth resources satellite. Spacecraft: Rohini. Decay Date: 1990-04-19 . USAF Sat Cat: 14002 . COSPAR: 1983-033A. Apogee: 485 km (301 mi). Perigee: 326 km (202 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. .

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