S5.98M
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Isayev N2O4/UDMH rocket engine. Used on Briz and Briz-M upper stages. Engine system consists of: main engine (2000 kgf, Isp=325.5s) + 4x11D458 (40 kgf, Isp=252s) + 12x17D58E (1.36 kgf, Isp=247s). 8 restarts. First flight 1990.
High performance storable liquid engine. Total deliverable impulse 2,000,000 kgf-s. Minimum impulse 2500 kg-s. Maximum burn time 1000 seconds; minimum time 1 second. Time between burns between 15 seconds and 5 hours. Vernier engines: 4 x 40 kgf. Specific impulse 275 sec. Total summary impulse 14,112 kg-s. Minimum impulse 4 kg-s. Orientation engines: 12 x 1.3 kgf. Specific impulse 270 sec. Minimum impulse 0.068 kg-s.
Engine: 95 kg (209 lb). Thrust to Weight Ratio: 21.05. Oxidizer to Fuel Ratio: 2. Restarts: 8.
Related
- Family
- Storable liquid
- Country
- Russia
- Spacecraft
- Angara Briz M
- Launch Vehicles
- Rokot, Proton/Briz K/M
- Propellants
- N2O4/UDMH
- Agency
- Isayev bureau