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BA-810
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Designer: Beal. Propellants: H2O2/Kerosene. Thrust(vac): 3,600.000 kN (809,300 lbf). Throttled thrust(vac): 1,800.000 kN (404,600 lbf). Isp: 282 sec. Burn time: 168 sec. Chambers: 1. Area Ratio: 25.13. Oxidizer to Fuel Ratio: 7.50. Country: USA. Status: Development 1990's. Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown.
BA-810 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...
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© Mark Wade, 1997 - 2007 except where otherwise noted.
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