 | Angara Khrunichev
Credit - Khrunichev
|
Orbital launch vehicle. Year: 1999. Family: Energia. Country: Russia. Status: In development. First planned upgrade of Angara, the 1.2 version would use a new Block I lox/kerosene upper stage. Manufacturer: Chelomei. LEO Payload: 3,700 kg (8,100 lb). to: 200 km Orbit. at: 63.00 degrees. Liftoff Thrust: 1,910.000 kN (429,380 lbf). Total Mass: 170,000 kg (370,000 lb). Core Diameter: 3.90 m (12.70 ft). Total Length: 42.90 m (140.70 ft).
Stage Data - Angara 1.2 - Stage Number: 1. 1 x Stage: Angara UM. Gross Mass: 140,000 kg (300,000 lb). Empty Mass: 10,000 kg (22,000 lb). Thrust (vac): 2,094.700 kN (470,907 lbf). Isp: 338 sec. Burn time: 300 sec. Isp(sl): 310 sec. Diameter: 2.90 m (9.50 ft). Span: 2.90 m (9.50 ft). Length: 25.00 m (82.00 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-191. Status: In development. Can be throttled to 95%. Propellant ration 2.6:1, chamber pressure 257 bar.
- Stage Number: 2. 1 x Stage: Angara A-2. Gross Mass: 25,200 kg (55,500 lb). Empty Mass: 2,355 kg (5,191 lb). Thrust (vac): 294.000 kN (66,093 lbf). Isp: 359 sec. Burn time: 300 sec. Diameter: 2.66 m (8.72 ft). Span: 2.66 m (8.72 ft). Length: 6.70 m (21.90 ft). Propellants: Lox/Kerosene. No Engines: 1. Engine: RD-0124. Status: In development. Two thrust levels. Propellant ration 2.6:1, chamber pressure 162 bar.
Bibliography and Further Reading - Kiselev, Anatoly I, introduction, Khrunichev State Research and Production Space Center, 1996. Colour brochure, in English and Russian, on the history and current products of the Russian space station manufacturer.
- Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...
|