RDMT-0.4 X
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
NII Mash N2O4/UDMH rocket engine. In Production. Experimental low-thrust thruster. Chamber from niobium alloy. Chamber pressure 41 / 17 bar. Specific impulse 313 / 302,3 sec.
Engine: 0.10 kg (0.22 lb). Chamber Pressure: 41.00 bar. Thrust to Weight Ratio: .4.
Related
- Family
- Storable liquid
- Country
- Russia
- Propellants
- N2O4/UDMH
- Agency
- NII Mash
- Bibliography
- 336