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RD-268


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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-268 Part of RD-215 Glushko N2O4/UDMH rocket engine. MR-UR-100 / RS-16 (SS-17) stage 1. Out of Production. First flight 1976. Modification of RD-263 engine. First flight 1990.

Status: Out of Production. Date: 1969-76. Thrust: 1,236.00 kN (277,863 lbf). Unfuelled mass: 770 kg (1,690 lb). Specific impulse: 319 s. Specific impulse sea level: 296 s. Height: 2.15 m (7.05 ft). Diameter: 1.08 m (3.55 ft).

Thrust (sl): 1,147.000 kN (257,855 lbf). Thrust (sl): 117,000 kgf. Engine: 770 kg (1,690 lb). Chamber Pressure: 226.00 bar. Thrust to Weight Ratio: 163.63. Oxidizer to Fuel Ratio: 2.67.

Family: Storable liquid. Country: Russia. Launch Vehicles: MR-UR-100. Propellants: N2O4/UDMH. Stages: MR-UR-100 St 1, Perimetr Stage 1. Agency: Glushko bureau. Bibliography: 342, 7515. Back to top of page Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
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