RD-861

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-861

RD-861
Credit: © Dietrich Haeseler

Yuzhnoye N2O4/UDMH rocket engine. Tsyklon 2 and 3 stage 3; Ikar. In production. Based on RD-854. Thrust vector control by 4 nozzles (thrust 98 N each) fed from a gas generator. First flight 1965.

AKA: 11D25;D-25;S5.23;S5.23, D-25. Status: In production. Date: 1968-72. Number: 229 . Thrust: 78.71 kN (17,695 lbf). Unfuelled mass: 123 kg (271 lb). Specific impulse: 317 s. Burn time: 130 s. Height: 1.56 m (5.11 ft). Diameter: 1.53 m (5.01 ft).

Mass given in ref. IAF-97-S.1.04 is 162 kg instead of 123 kg originally stated.

Chambers: 1 + 4 + 2. Engine: 123 kg (271 lb). Chamber Pressure: 88.80 bar. Area Ratio: 112.4. Thrust to Weight Ratio: 65.25. Oxidizer to Fuel Ratio: 2.1.

Family: Storable liquid. Country: Ukraine. Launch Vehicles: Tsiklon-2, Tsiklon-3. Propellants: N2O4/UDMH. Stages: Tsyklon 2-3, Tsyklon 3-3. Agency: Yuzhnoye. Bibliography: 326, 348, 42, 4477.

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