|
Engine Model: Agni. Designer: DRDO. Gross Mass: 11,500 kg (25,300 lb). Empty Mass: 2,900 kg (6,300 lb). Propellants: Solid. Thrust(vac): 700.000 kN (157,360 lbf). Burn time: 50 sec. Diameter: 1.00 m (3.20 ft). Length: 11.00 m (36.00 ft). Country: India.
Engine Model: SLV-1. Designer: ISRO. Gross Mass: 10,800 kg (23,800 lb). Empty Mass: 2,140 kg (4,710 lb). Propellants: Solid. Thrust(vac): 502.600 kN (112,989 lbf). Thrust(sl): 454.900 kN (102,266 lbf). Isp: 253 sec. Isp (sea level): 229 sec. Burn time: 49 sec. Diameter: 1.00 m (3.20 ft). Length: 9.99 m (32.77 ft). Chambers: 1. Chamber Pressure: 43.00 bar. Area Ratio: 6.70. Country: India. First Flight: 1979. Last Flight: 2003. Flown: 64.
Agni used on Rocket Stages
- Used on stage: SLV-1. on launch vehicle: ASLV.
- Used on stage: SLV-1. on launch vehicle: PSLV.
- Used on stage: SLV-1. on launch vehicle: SLV.
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2008 except where otherwise noted.
|
|