|
BA-3200
|
|
Designer: Beal. Propellants: H2O2/Kerosene. Thrust(vac): 14,100.000 kN (3,169,800 lbf). Throttled thrust(vac): 9,870.000 kN (2,218,860 lbf). Isp: 259 sec. Burn time: 131 sec. Chambers: 1. Area Ratio: 6.48. Oxidizer to Fuel Ratio: 7.00. Country: USA. Status: Development 1990's. Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 70% of initial value before shutdown.
BA-3200 used on Rocket Stages
Bibliography and Further Reading - Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004. ISBN: 156347591X. The best reference on launch vehicles ever produced. More at amazon.com...
|
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.
|
|
|
|