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RD-0750

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-0750 Part of RD-0120 Kosberg LOx/LH2/kerosene rocket engine. Alternative for Angara central stage, MAKS. Developed 1997-. Tripropellant derivative of RD-0120. Some components tested in RD-0120TD technology demonstration in cooperation with Aerojet. AKA: RD-0650TF. Status: Developed 1997-. Date: 1997-. Thrust: 1,412.00 kN (317,430 lbf). Specific impulse: 455 s. Specific impulse sea level: 415 s. Two modes: LOX/LH2-Kerosene and LOX/LH2. Chamber pressure 190 / 85 bar. O:F ratio 4.0 / 6.0. The original source gave different thrust and specific impulse items. Those shown here are from the 2007 KBKhA web site (original values thrust 1720 kN / 780 kN, specific impulse 418 sec / 451 sec. Throttled thrust(vac): 794.600 kN (178,633 lbf). Chamber Pressure: 190.00 bar. Oxidizer to Fuel Ratio: 4. Country: Russia. Propellants: Lox/Kerosene/LH2, Lox/LH2. Agency: Kosberg bureau. Bibliography: 342, 352, 4484. 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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