Beal H2O2/Kerosene rocket engine. 3600 kN. Development 1990's. Pressure-fed engine with composite ablative chamber and nozzle. Helium pressurant. Thrust declines to 50% of initial value before shutdown. Isp=282s.
Throttled thrust(vac): 1,800.000 kN (404,600 lbf). Area Ratio: 25.13. Oxidizer to Fuel Ratio: 7.5.
Status: Development 1990's.
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Thrust: 3,600.00 kN (809,300 lbf).
Specific impulse: 282 s.
Burn time: 168 s.
Associated Manufacturers and Agencies
Beal American manufacturer of rocket engines and rockets. Beal, USA. More...
H2O2/Kerosene Hydrogen peroxide is used as both an oxidiser and a monopropellant. Relatively high density and non-toxic, it was abandoned after early use in British rockets, but recently revived as a propellant for the Black Horse spaceplane. Rocket propellant RP-1, or its foreign equivalents, is a straight-run kerosene fraction, which is subjected to further treatment, i.e., acid washing, sulphur dioxide extraction. Thus, unsaturated substances which polymerise in storage are removed, as are sulphur-containing hydrocarbons. More...
Isakowitz, Steven J, Hopkins, Joshua B, and Hopkins, Joseph P, International Reference to Space Launch Systems, AIAA, Washington DC, 2004.
Beal BA-2 Stage 2 H2O2/Kerosene propellant rocket stage. Loaded/empty mass 189,000/14,560 kg. Thrust 3,599.00 kN. Vacuum specific impulse 282 seconds. Thrust declines to 50% of initial value at shut down. More...
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