摘要
用辨识方法确定了带反喷固体火箭发动机推力终止过程中的瞬变参数，视这些参数是服从正态分布的随机变量，用Montecarlo方法分析了推力终止过程内弹道的散布。结果显示，推力终止过程中不同时刻压力散布服从正态分布，据此求出了弹道散布的数字特征和分布函数，研究结果对带反喷管的固体火箭发动机设计有参考价值。
As the transient parameters during thrust termination of SRM with four reverse nozzles are determined by identification techniques and considered as random variables which obey normal distribution, the interior ballistic dispersion during thrust termination can be analyzed by Monte Carlo method. The reults show that the pressure dispersion obeys normal distribution. The digital characteristic parameters and distribution function are also determined in this paper. This study is useful for the design of SRM with reverse nozzle.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1997年第6期31-35,共5页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
内弹道计算
随机取样
Solid propellant rocket motor, Interior ballistic calculation, Random scanning,Computerized simulation, Parameter identification
