RD-0242
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: KBKhA
Kosberg N2O4/UDMH rocket engine. sea-based missile booster stage developed 1977-83 (Burlak). First concept planned N2O4/kerosene as propellant, but changed to N2O4/UDMH. Single ignition, 297 development tests. 50 engines for sale.
Max. duration 420 s.
Engine: 120 kg (260 lb). Chamber Pressure: 196.20 bar. Thrust to Weight Ratio: 105.03.
Subtopics
- RD-0242-HC Kosberg LOx/Kerosene rocket engine. Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
- RD-0242M Kosberg N2O4/MMH rocket engine. Design concept 1998-. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH. Reusable for 6 ignitions total. Throttling to 80%.
- RD-0242M1 Kosberg N2O4/MMH rocket engine. Design concept 1998-. Proposed variant of RD-0242 engine for upper stages using MMH in place of UDMH (adaptation to western market). Reusable for 6 ignitions total. Throttling to 80%.
Related
- Family
- Storable liquid
- Country
- Russia
- Propellants
- N2O4/UDMH
- Agency
- Kosberg bureau