SLV
Launch vehicle · India
Original archive entry. The text, images and links below are kept as they were written.
Indian all-solid orbital launch vehicle.
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
Related
- Family
- all-solid, orbital launch vehicle
- Country
- India
- Stages
- SLV-3 engine, SLV-1, SLV-2, SLV-4
- Agency
- ISRO
Chronology
4 events
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. .