RD-0126
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: KBKhA
Kosberg LOx/LH2 rocket engine. Space tugs or upper stage for Onega or Yastreb versions of Soyuz. Single annular chamber with expansion-deflection nozzle, separate turbopumps. Design concept 1993. Hot-tests in 1998.
Engine: 320 kg (700 lb). Chamber Pressure: 71.50 bar. Thrust to Weight Ratio: 12.49. Oxidizer to Fuel Ratio: 6.
Subtopics
- RD-0126E Kosberg LOx/LH2 rocket engine. Upper stages. Design concept 1998-. Concept for a cryogenic engine for upper stages. Single annular chamber with straight expansion nozzle, common turbopump.
Related
- Country
- Russia
- Launch Vehicles
- Onega
- Propellants
- Lox/LH2
- Agency
- Kosberg bureau