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RD-0142


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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-0142 Part of RD-0120 Kosberg LOx/LNG rocket engine. stage 2. Developed 1998-on. Proposed engine for LOX/liquid natural gas. Staged combustion cycle. Obviously variant of RD-0141 with larger nozzle.

Status: Developed 1998-on. Date: 1998-. Thrust: 2,353.00 kN (528,975 lbf). Unfuelled mass: 2,058 kg (4,537 lb). Specific impulse: 369 s. Height: 4.51 m (14.79 ft).

Engine: 2,058 kg (4,537 lb). Thrust to Weight Ratio: 116.56.

Country: Russia. Propellants: Lox/LNG. Agency: Kosberg bureau. Bibliography: 403. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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