RD-120K
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko LOx/Kerosene rocket engine. Soyuz M stage 1, 2. Proposed for X-34. Sea-level variant of RD-120. As of 1996 RD-120 prototype with 1.8 m diameter had been built, development time estimated for three years.
Thrust and Isp range due to throat diameter and chamber pressure. Gimbaling +/- 6 degree in two planes. Chamber pressure 163 - 172 bar.
Throttled thrust(vac): 794.000 kN (178,498 lbf). Thrust (sl): 866.900 kN (194,887 lbf). Thrust (sl): 88,396 kgf. Engine: 1,433 kg (3,159 lb). Chamber Pressure: 172.00 bar. Thrust to Weight Ratio: 62.1. Oxidizer to Fuel Ratio: 2.6.
Related
- Country
- Russia
- Launch Vehicles
- Soyuz M
- Propellants
- Lox/Kerosene
- Stages
- Kvant-1 stage, Kvant-1-1, Soyuz M-0, Soyuz M-1
- Agency
- Glushko bureau