| 摘要 |
A hybrid heater vaporization system (280, 380) including hybrid heaters (250, 350) can be used to vaporize liquid oxygen as it enters a motor (200, 300) to improve the combustion characteristics of a hybrid rocket (11). The motor (200, 300) preferably includes hybrid fuel both in a substantially cylindrical portion (216, 316) in the substantially cylindrical portion of the motor and a substantially multi-toroidal shaped portion (217, 316) in the forward end of the motor (200, 300). The vaporization system (280, 380) of the present invention finally makes hybrid rockets (11) practical for aerospace applications.
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