RD-0204
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Hardware. Diameter is per chamber. Staged combustion cycle. Variant of RD-0203 with additional pressure sensor. First flight 1964.
Thrust (sl): 500.000 kN (112,400 lbf). Thrust (sl): 51,000 kgf. Engine: 381 kg (839 lb). Area Ratio: 29.8. Thrust to Weight Ratio: 149.5. Oxidizer to Fuel Ratio: 2.6.
Related
- Family
- Storable liquid
- Country
- Russia
- Propellants
- N2O4/UDMH
- Stages
- UR-200-1
- Agency
- Kosberg bureau