摘要
本文介绍一个反向喷管推力终止的冷模拟实验.实验表明,突然打开固体火箭发动机反向喷管后,燃烧室中可能出现强烈的压力冲击,这种压力冲击来自喷管喉部节流和形成准稳态流动之前的非定常过程.本文对这一效应做了估算.用特征线法及激波拟合法进行了一维非定常流动的数值分析.预估的压力-时间曲线与实验结果相当一致.
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.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1989年第4期1-6,共6页
Journal of Propulsion Technology
关键词
推力终止
固体推进剂
火箭发动机
内弹道
喷管
Thrust termination, Solid rocket engine, Interior trajectory calculation,Thrust deflector, Thrust reverser
