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RD-192

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-192 Part of RD-170 Glushko LOx/LCH4 rocket engine. Proposed methane-variant of RD-191. Gimbaling +/- 8 degree in two planes. In 1996 prototype development was estimated to take four years from go-ahead. Nozzle expansion ratio is 262/0.75=349. Status: Developed 1996-. Date: 1996-. Thrust: 2,138.00 kN (480,641 lbf). Unfuelled mass: 3,300 kg (7,200 lb). Specific impulse: 356 s. Specific impulse sea level: 330 s. Height: 4.05 m (13.28 ft). Diameter: 2.00 m (6.50 ft). Engine: 3,300 kg (7,200 lb). Chamber Pressure: 257.00 bar. Thrust to Weight Ratio: 66.06. Oxidizer to Fuel Ratio: 3.5. Country: Russia. Propellants: Lox/LCH4. Agency: Glushko bureau. Bibliography: 325, 402. 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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