固体发动机真空比冲分析

VACUUM SPECIFIC IMPULSE ANALYSIS FOR A SOLID ROCKET MOTOR

关键词:  固体火箭发动机  比冲  推进剂试验

Key words:  Solid rocket engine  Specific impulse  Propellant test

摘要:

本文预示了SRM-1、SRM-2和SRM-3固体发动机的真空比冲效率(或无因次比冲),并对前两种高模试车失败的发动机进行了分析,所得实测真空比冲效率与预示值基本一致,相对偏差均未超过0.3%.同时,通过真空比冲数学模型及模拟参数分析,得出了缩比试验发动机不能模拟的三个主要参数(L~*,d_t,t_b)及实施模拟的办法.在此基础上提出了大型发动机带缩比试验发动机进行高模试车的建议.

Abstract:

The vacuum specific impulse efficiencies for SRM-1,SRM-2 and SRM-3 are predicted separately in the paper.The predicted values of specific impulse efficiencies are coordinated with the measured ones well and the their relative deviations are not more than 0.3% .Simultaneously,un-simulated three principal parameters (L,d1, tb) for the small-scale motor were found by analysing of the simulated parameters in the mathematical modle of vacuum specific impulse.As a result,the alternated method for predicting the vacuum specific impulse efficiencies of the small-scale motor was implemented.On the basis of this,the proposal to use the full-scale motor with the simulated small-scale motor for the high-altitude simulation test is presented.