KTDU-80
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Isayev N2O4/UDMH rocket engine. Soyuz TM, Progress M. In Production. Propulsion system included 4 spherical tanks for a total of 880 kg propellant. Developed from NII Mash experimental thruster. 3 thrust levels by 4 valves.
Three thrust levels by 4 valves: 6000 N, 0.7 N, 0.3 N. Specific impulse 326 - 286 sec.
Engine: 310 kg (680 lb). Chamber Pressure: 8.80 bar. Area Ratio: 153.8. Thrust to Weight Ratio: 2.03. Oxidizer to Fuel Ratio: 1.85.
Related
- Family
- Storable liquid
- Country
- Russia
- Spacecraft
- Soyuz TM, Progress M, Soyuz TMA, Soyuz TMA PAO
- Propellants
- N2O4/UDMH
- Agency
- Isayev bureau