RD-134
Engine · Russia
Original archive entry. The text, images and links below are kept as they were written.
Glushko LOx/Kerosene rocket engine. upper stage. Design concept. Proposed upper stage kerosene engine. Gimbaling +/- 3 degree in two planes. Four chamber s with one common turbopump. Nozzle expansion ratio is 170/0.05=3400.
In 1996 prototype development was estimated to take four years from go-ahead.
Chambers: 4. Engine: 540 kg (1,190 lb). Chamber Pressure: 167.00 bar. Thrust to Weight Ratio: 64.81. Oxidizer to Fuel Ratio: 2.6.
Subtopics
- RD-134R Glushko LOx/Kerosene rocket engine. Angara stage 2 vernier. Design concept 1993-on. Proposed in initial study for Angara by RKK Energia in1993. Steering engines for Angara upper stage. Kerosene RG-1.
- RD-167 Glushko LOx/LCH4 rocket engine. Upper stage. Design concept 1990's. Proposed upper stage engine, a methane variant of RD-134. Gimbaling +/- 3 degree in two planes. Four chambers with one common turbopump.
Related
- Country
- Russia
- Propellants
- Lox/Kerosene
- Agency
- Glushko bureau