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

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

New arrangement of turbine exhaust lines for improved performance.

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.

Family: Storable liquid. Country: Ukraine, Italy. Launch Vehicles: Vega. Propellants: N2O4/UDMH. Agency: Yuzhnoye, Fiat-Avio.
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