This page no longer updated from 31 October 2001. Latest version can be found at www.astronautix.com
Designer: Beal. Used on stages: Beal BA-2 Stage 3. Propellants: H2O2/Kerosene Thrust(vac): 20,000 kgf. Thrust(vac): 196.00 kN. Isp: 300 sec. Burn time: 600 sec. Chambers: 1. Area Ratio: 100.00. Oxidizer to Fuel Ratio: 7.50. Country: USA. Status: Development. References: 455 . Comments: Pressure-fed restartable engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown.
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 .