Encyclopedia Astronautica
RD-861G


Yuzhnoye, Fiat Avio N2O4/UDMH rocket engine. 76.453 kN. Vega upper stage. Developed 1996-. Isp=325s. Proposed uprate of RD-861 engine. Thrust vector control by gimbal, roll control by 4 nozzles (thrust 29 N each).

New arrangement of turbine exhaust lines for improved performance.

Application: Vega upper stage.

Characteristics

Chambers: 1 + 4. Engine: 185 kg (407 lb). Chamber Pressure: 88.80 bar. Area Ratio: 112.4. Thrust to Weight Ratio: 42.14. Oxidizer to Fuel Ratio: 2.41.

AKA: 11D25G.
Status: Developed 1996-.
Unfuelled mass: 185 kg (407 lb).
Height: 1.66 m (5.46 ft).
Thrust: 76.45 kN (17,187 lbf).
Specific impulse: 325 s.
Burn time: 400 s.
First Launch: 1996-.

More... - Chronology...


Associated Countries
See also
Associated Launch Vehicles
  • Vega Primarily Italian all-solid propellant launch vehicle. After years of furious debate, a $173 million development program began, 52% funded by Italy and 34% by France. As of the first firing of the P80 first stage motor at the end of 2006, first flight had slipped into 2008 from a 2007 original planned date. More...

Associated Manufacturers and Agencies
  • Yuzhnoye Ukrainian manufacturer of rockets, spacecraft, and rocket engines. Yangel Design Bureau, Dnepropetrovsk, Ukraine. More...

Associated Propellants
  • N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...

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