ACOUSTIC CAVITY MANIFOLD FOR ROCKET ENGINE, ROCKET ENGINE, AND METHOD FOR IMPROVING EFFICIENCY OF SPECIFIC IMPULSE OF ROCKET ENGINE

摘要

PROBLEM TO BE SOLVED: To provide a thruster for controlling attitude and changing direction capable of improving the efficiency of specific impulse without increasing heat load of a combustion device and reducing the performance of a bipropellant combustion device of natural type.;SOLUTION: A reinforcing gas supply device 24 is provided with the acoustic cavity manifold 30 attached between an outer fringe 34 of a face 36 of an injector and a combustion chamber 12. The reinforcing gas is injected into the combustion chamber 12 from a tank 26 for reinforcing gas through the acoustic cavity manifold 30 by the reinforcing gas supply device 24. A boundary layer is formed between a combustion gas stream and a wall part 14 of the chamber by injection of reinforcing gas to reduce heat load of the wall part 14 of the chamber and improve specific impulse of the rocket engine 10. Active element such as hydrogen and inactive element such as helium can be used as the reinforcing gas. Consequently, the efficiency of specific impulse is improved without reducing performance.;COPYRIGHT: (C)2007,JPO&INPIT