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-0207
Kosberg N2O4/UDMH rocket engine. UR-200 stage 2 vernier. Developed 1961-64. Gas generator cycle. Four vernier thrusters. First flight 1964.

AKA: 8D67. Status: Developed 1961-64. Date: 1961-64. Thrust: 30.90 kN (6,947 lbf). Specific impulse: 297 s. Burn time: 133 s. Diameter: 0.16 m (0.53 ft).

Chambers: 4. Chamber Pressure: 53.00 bar. Area Ratio: 43.3. Oxidizer to Fuel Ratio: 1.8.



Subtopics

RD-0214 Kosberg N2O4/UDMH rocket engine. Proton stage 3 vernier. In Production. Based on RD-0207. Four used as steering engines for Proton Stage 3 in system RD-0212. First flight 1967.

Family: Storable liquid. Country: Russia. Propellants: N2O4/UDMH. Stages: UR-200-2. Agency: Kosberg bureau. Bibliography: 309, 320, 7476.

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
© 1997-2017 Mark Wade - Contact
© / Conditions for Use