关键词: 推力终止;固体火箭发动机;内弹道计算;推力换向器;反推力装置

Abstract: A cold air experiment on thrust termination of a solid rocket motor with reversal nozzles is described in this paper.It’s verified that a series of intense pressure impulses can occur in the combustion chamber after the thrust reversal nozzles of the solid rocket motor are suddenly opened. These impulses come from the unsteady process prior to the throat chocking and the formation of a quasi-steady flow in the reversal nozzles. This effect is estimated, based on numerical analysis of one-dimensional unsteady flow by the characteristics method and the shock fitting method. The prediction of pressure-time history is in good agreement with the experimented results.

Key words: Thrust termination;Solid rocket engine;Interior trajectory calculation;Thrust deflector;Thrust reverser