This page no longer updated from 31 October 2001. Latest version can be found at RD-861G

Manufacturer Name: RD-861G. Government Designation: 11D25G. Designer: Yuzhnoye + Fiat Avio. Developed in: 1996-. Application: Vega upper stage. Propellants: N2O4/UDMH Thrust(vac): 7,796 kgf. Thrust(vac): 76.45 kN. Isp: 325 sec. Burn time: 400 sec. Mass Engine: 185 kg. Length: 1.7 m. Chambers: 1 + 4 + 2. Chamber Pressure: 88.80 bar. Area Ratio: 112.40. Oxidizer to Fuel Ratio: 2.41. Country: Ukraine + Italy. Status: Developed 1996-. References: 326 . Comments: 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.
Back to Index
Last update 12 March 2001.
Definitions of Technical Terms.
Contact Mark Wade with any corrections or comments.
Conditions for use of drawings, pictures, or other materials from this site..
© Mark Wade, 2001 .