|
RD-0242-HC
|
|
Manufacturer Name: RD-0242-HC. Designer: Kosberg. Developed in: 1998-. Propellants: Lox/Kerosene. Thrust(vac): 125.000 kN (28,101 lbf). Isp: 312 sec. Mass Engine: 120 kg (260 lb). Chambers: 1. Chamber Pressure: 196.20 bar. Oxidizer to Fuel Ratio: 2.60. Thrust to Weight Ratio: 106.21. Country: Russia. Status: Developed 1998-. Proposed variant of RD-0242 engine using LOX-kerosene instead of N2O4/UDMH as propellants.
Bibliography and Further Reading - Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
|
Contact us with any corrections, additions, or comments.
Conditions for use of drawings, pictures, or other materials from this site..
To contact astronauts or cosmonauts.
© Mark Wade, 1997 - 2007 except where otherwise noted.
|
|
|
|