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RD-0225

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-0225 RD-0225 Almaz engine RD-0225 main propulsion engine for Almaz space station Credit: © Dietrich Haeseler Kosberg N2O4/UDMH rocket engine. Almaz space station orbital maneuvering. Hardware. Originally designed for UR-100 follow-on spaceships. Two engines used on Almaz space station for orbital maneuvering, Pressure fed. First flight 1974. AKA: 11D24. Status: Hardware. Date: 1966-71. Thrust: 3.92 kN (882 lbf). Unfuelled mass: 23 kg (50 lb). Specific impulse: 287 s. Burn time: 1,200 s. Height: 1.00 m (3.27 ft). Diameter: 0.46 m (1.50 ft). Engine: 23 kg (50 lb). Chamber Pressure: 8.80 bar. Area Ratio: 64. Thrust to Weight Ratio: 17.39. Oxidizer to Fuel Ratio: 1.85. Subtopics RD-0237 Kosberg N2O4/UDMH rocket engine. UR-100N / RS-18 (SS-19) stage 3. MIRV service block. Open cycle. Analogous to RD-0225, pressure fed. Steering engine for space vehicles gimbaling +/- 45 degree. First flight 1972. Family: Storable liquid. Country: Russia. Spacecraft: Almaz APOS, Almaz OPS-2, Almaz OPS, Almaz-T, Almaz-1B, Almaz-2. Launch Vehicles: Proton. Propellants: N2O4/UDMH. Stages: Proton KM-4. Agency: Kosberg bureau. Bibliography: 307, 95. Photo Gallery RD-0225 Credit: KBKhA 8K84 back Credit: © Mark Wade Back to top of page 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 © 1997-2019 Mark Wade - Contact © / Conditions for Use

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