RD-0126A

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

RD-0126A

Part of RD-0131

RD-0126E
Credit: KBKhA

Kosberg LOx/LH2 rocket engine. Upper stages. Design concept 1996-. Concept for a cryogenic engine for upper stages. Single annular chamber with expansion-deflection nozzle, common turbopump.

AKA: RO-97A. Status: Design concept 1996-. Date: 1996-. Thrust: 98.00 kN (22,031 lbf). Unfuelled mass: 340 kg (740 lb). Specific impulse: 476 s. Height: 2.73 m (8.95 ft).

Engine: 340 kg (740 lb). Chamber Pressure: 118.00 bar. Thrust to Weight Ratio: 29.41. Oxidizer to Fuel Ratio: 6.

Country: Russia. Propellants: Lox/LH2. Agency: Kosberg bureau.

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z