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-0205
Part of RD-0202
RD-0205 8D46

RD-0205 8D46
RD-0205 8D46 on stage 8S816 (UR-200)
Credit: © Mark Wade
Kosberg N2O4/UDMH rocket engine. UR-200 stage 2. Engine unit consisting of 1 RD-0206 main engine and 4 RD-0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle. Developed 1961. First flight 1963.

AKA: 8D46. Date: 1961-64. Number: 9 . Thrust: 606.40 kN (136,324 lbf). Gross mass: 622 kg (1,371 lb). Unfuelled mass: 552 kg (1,216 lb). Specific impulse: 322 s. Burn time: 150 s. Height: 2.33 m (7.63 ft). Diameter: 1.47 m (4.82 ft).

Engine: 552 kg (1,216 lb). Area Ratio: 48.07. Thrust to Weight Ratio: 113.2. Oxidizer to Fuel Ratio: 2.625.

Family: Storable liquid. Country: Russia. Launch Vehicles: Initial UR-500, UR-200. Propellants: N2O4/UDMH. Stages: UR-200-2. Agency: Kosberg bureau. Bibliography: 309, 7474.
Photo Gallery
RD-0205RD-0205
Credit: KBKhA
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