RD-56
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Isayev LOx/LH2 rocket engine. N1 block R. Development ended 1971. Oxygen-hydrogen engine for cryogenic upper stage. Developed but never flown. Design sold to India in 1990's for GSLV.
Engine: 282 kg (621 lb). Chamber Pressure: 55.90 bar. Area Ratio: 198.7. Thrust to Weight Ratio: 25.17. Oxidizer to Fuel Ratio: 6.
Subtopics
- RD-56M Isayev LOx/LH2 rocket engine. Originally developed for Proton and Angara upper stage KVRB with planned first flight 1995. Finally flown on 12KRB upper stage for India's GSLV. First flight 2001.
- RD-56M LNG Isayev LOx/LNG rocket engine. Vozdushnyy Start stage 2. Developed 1996-. Variant of RD-56M using liquid natural gas in place of hydrogen. First engine tests performed in 1998.
Related
- Country
- Russia
- Propellants
- Lox/LH2
- Stages
- N1 Block R
- Agency
- Isayev bureau