R-40B R-40B Credit - Aerojet Redmond Designer: Aerojet Redmond. Propellants: N2O4/MMH. Thrust(vac): 4.000 kN (899 lbf). Isp: 293 sec. Burn time: 23,000 sec. Mass Engine: 7.23 kg (15.93 lb). Diameter: 0.40 m (1.32 ft). Length: 0.71 m (2.33 ft). Chambers: 1. Chamber Pressure: 10.34 bar. Area Ratio: 60.00. Country: USA. Status: In Production.                   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.

Encyclopedia Astronautica topic index 0 - A - B - C - D - E - F - G - H - I - J - K - L - M - N - O - P - Q - Ra - Re - Sa - Sf - Sp - T - U - V - W - X - Y - Z Enter your search terms   Web www.astronautix.com Submit search form