RD-0124
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Credit: KBKhA
Kosberg LOx/Kerosene rocket engine. In development. Engine to succeed RD-0110 in second stage of Soyuz. Used staged combustion; chamber pressure increased from 70 to 160 bar, specific impulse from 326 to 359 seconds. First flight 2001. Proposed for small launcher Kvant-1 by RKK Energia for stage 1 steering engine. Also proposed by RKK Energia in initial studies in 1993 for Angara upper stage.
Payload increase by 950 kg from current 6900 / 7200 kg from Plesetsk / Baikonur.
Chambers: 4. Engine: 480 kg (1,050 lb). Chamber Pressure: 162.00 bar. Propellant Formulation: Lox/RG-1. Thrust to Weight Ratio: 62.5. Oxidizer to Fuel Ratio: 2.6.
Related
- Country
- Russia
- Launch Vehicles
- Soyuz M, Soyuz-ST-B
- Propellants
- Lox/Kerosene
- Stages
- Angara A-2, Soyuz ST-2
- Agency
- Kosberg bureau