固体火箭发动机性能分析及预示

Performance Analysis and Prediction of SRM

根据固体火箭发动机地面及高空模拟试验,提出了内弹道性能分析及预示方法,并编制了程序.通过算例给出了某发动机内弹道性能P-t、F-t、q_m-t、I_s-t、m_p-t曲线及试验修正系数k_1、ξ_(C_*)和ξ_(CF).计算表明,理论预示推力与测试推力基本一致,平均推力偏差不大于0.4%,平均比冲偏差不大于0.35%.由该程序计算的内弹道性能可提供导弹总体设计使用.

This article puts forward a kind of methods of the performance analysis and prediction of internal ballistics of SRM, and compiles the calculating programs, according to the results of static firing test and simulated altitude test of SRM. The P-t, F-t, q_m - t, I_s-t, m_p- t curves and the k_1 ξ_c and ξ_CF test coefficients of a solid rocket motor are gained by calculating. By calculating, we can gain the curve of prediction thrust, which is about the same as the curve of practical survey. And thrust deviation is less than 0.4%, the specific impulse deviation is less than 0.35%. The result of internal ballistics performance is used in total design of missile.