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RD-857
Credit - via Dietrich Haeseler
Engine Model: RD-857. Manufacturer Name: RD-857. Government Designation: 15D12. Designer: Yuzhnoye. Developed in: 1963-67. Application: Combined missile (RT-20P) stage 2. Propellants: N2O4/UDMH. Thrust(vac): 137.300 kN (30,866 lbf). Isp: 330 sec. Burn time: 215 sec. Mass Engine: 190 kg (410 lb). Diameter: 0.93 m (3.04 ft). Length: 2.10 m (6.80 ft). Chambers: 1. Chamber Pressure: 127.50 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 73.68. Country: Ukraine. Status: Out of production. First Flight: 1967. Last Flight: 1969. Flown: 12.

Designed for second stage of combined missile, only flight tests. Thrust vector control by secondary gas injection into nozzle. Second thrust level at 12.75 kN.

RD-857 used on Rocket Stages
Bibliography:

  • Rakhmanin, V F, Odnazhdy i Navsegda, NPO Energomash, Moscow 1998 via Dietrich Haeseler.
  • Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: http://home.earthlink.net/~cliched/main_space.html.
  • Shnyakin, V N, Shidkostnye Raketye Dvigateli - Opisanie i Osnovnye Tekhnicheskie Dannye, GKB Yuzhnoe "Yangel", Dnepropetrovsk 1996 via Dietrich Haeseler.
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