摘要
利用发动机地面试验结果,引入广义的压强系数和推力系数,计算了发动机的特征速度、喷管喉部面积等参数。在此基础上利用随机试件和标准发动机的相关参数预示了发动机的压强、推力、流量及其积分。通过算例可以看出,此发动机内弹道性能工程预示方法简单实用,预示精度满足要求。
The characteristic velocity, area of nozzle throat and other parameters are calculated by using the static test results of solid rocket motor (SRM) and introducing generalized pressure coefficient and thrust coefficient. Based on this , SRM' s pressure, thrust, mass flow rate and their integration sum are predicted with correlation parameters of random specimen and standard motor. The results show that the engineering method is simple and useful, and the prediction accuracy meets demand.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2003年第3期11-13,17,共4页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
内弹道
工程预示方法
压强
推力
solid propellant rocket engine
interior ballistic per- formance
engineering foreshow method
