大长径比固体火箭发动机点火瞬态过程性能散布分析  

Analysis on ignition transient performance distribution of large L/D ratio solid rocket motors

作　　者：钟涛[1] 王中伟[1] 张为华 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2005年第2期98-100,共3页Journal of Solid Rocket Technology

基　　金：国家863高新技术项目资助(2003AA765030)

摘　　要：采用均匀设计方法设计数值试验,研究大长径比固体火箭发动机点火瞬态过程性能散布特性,利用逐步回归法得到堵盖打开时间、推进剂初焰时间、点火压强峰值及时间4个性能参数与散布影响因素的回归关系式,分析了各项性能散布指标与其主要影响因素的关系。结果表明,堵盖打开时间散布取决于堵盖强度,推进剂初焰时刻散布由其着火临界温度控制,点火瞬态压强峰值时刻散布由推进剂密度和喷喉直径控制,点火压强峰值散布主要受推进剂密度、着火临界温度和喷喉直径的影响;并提出了降低散布的工程措施。By using uniform design numerical experiment method, the characteristics of ignition transient performance distribution of large L/D ratio solid rocket motors was investigated. Then the stepwise regression method was used to obtain regression equation among four performance parameters and influence factors of distribution, such as blow-out time of closure, the first flame time of propellant, ignition pressure peak value and time. The relations among all performance distribution indexes and main influence factors were investigated. The results show that distribution of closure blow-out time depends on closure strength, distribution of the first flame of propellant is controlled by ignition critical temperature, and distribution of ignition transient pressure peak value is controlled by propellant density and throat diameter, and distribution of ignition pressure peak value is mainly determined by propellant density, ignition transient temperature and throat. The engineering measures are put forward to reduce the distribution.

关 键 词：固体推进剂火箭发动机 点火瞬态过程 性能散布 均匀设计 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]