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RD-861G
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Manufacturer Name: RD-861G. Government Designation: 11D25G. Designer: Yuzhnoye + Fiat Avio. Developed in: 1996-. Application: Vega upper stage. Propellants: N2O4/UDMH. Thrust(vac): 76.453 kN (17,187 lbf). Isp: 325 sec. Burn time: 400 sec. Mass Engine: 185 kg (407 lb). Length: 1.66 m (5.46 ft). Chambers: 1 + 4. Chamber Pressure: 88.80 bar. Area Ratio: 112.40. Oxidizer to Fuel Ratio: 2.41. Thrust to Weight Ratio: 42.14. Country: Ukraine + Italy. Status: Developed 1996-. Proposed uprate of RD-861 engine. Thrust vector control by gimbal, roll control by 4 nozzles (thrust 29 N each) and new arrangement of turbine exhaust lines for improved performance.
Bibliography and Further Reading - Shnyakin, Klimov, Shulga, IAF-Congress Turin, 1997, "Uprated Main Liquid Propellant Rocket Engine For CYCLONE LV Third Stage", IAF-97-S.1.04 via Dietrich Haeseler.
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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