固体火箭发动机推力终止过程的数值分析

THE NUMERICAI ANAIYSIS OF THE THRUST TERMINATION PROCESS IN SOLID ROCKET MOTORS

本文指出,在大、中型固体火箭发动机的推力终止过程中,打开反向喷管(或辅助排气孔)必定导致产生一系列强度相当大的压力脉冲,而现有的理论分析均不能预估和解释这一现象。本文提供了一组冷模拟实验结果,讨论了产生压力脉冲的原因,提出了估算其强度的方法,并且应用特征线法和激波拟合法进行一维非定常流动的数值计算,发展了一种能够同时预估压力脉冲强度的内弹道计算程序。预估结果与实验曲线吻合良好。

It is pointed out that a series of pressure pulses with considerable strength will follow after opening the reversal nozzle (or auxiliary exhaust hole) in the thrust termination process of large or middle-scale solid rocket motors. Since no theoretical analysis is able to explain or predict these phenomena, this paper cites a series of cool simulation testing results, discusses the reasons for the appearance of pressure pulses, and put forward the methods to estimate the pulse strength. Furthermore, an interior ballistics computer program which can be also applied to estimate the strength of pressure pulses is developed by utilizing the Characteristics Method and the Shock Fitting method for the numerical analysis of One-dimensional unsteady flow. The predicted results are in gcod agreement with the experimental curves.