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针对新一代火箭上面级膨胀循环发动机使用的钝感点火器,为评估点火器的可靠性水平,通过点火器验收试验获取的强烈燃烧时间数据和膨胀循环发动机试车获取的起动加速性数据,利用假设检验的方法证明发动机建压时间S和点火器强烈燃烧时间r都呈正态分布状态,根据概率统计理论,其差r-s也为正态分布。采用应力-强度分布干涉理论,分析计算点火器基于发动机试车时序的点火可靠性为0.999 970。根据本文的分析和计算,认为验收的点火器发火性能可靠,能够保证发动机建压的可靠性,点火器强烈燃烧时间能满足发动机系统要求。
In order to evaluate the reliability level of the igniter, the data of the intense combustion time obtained by the igniter acceptance test and the starting acceleration data obtained by the test run of the expansion cycle engine, aiming at the ignited igniter used in the new generation rocket upper stage expansion cycle engine, The test method proves that the engine build pressure time S and igniter strong combustion time r are in a normal distribution. According to the theory of probability statistics, the difference rs is also a normal distribution. Based on the theory of stress-intensity distribution interference, the ignition reliability based on engine test sequence is analyzed and calculated as 0.999 970. According to the analysis and calculation of this article, it is considered that the igniter of the acceptance is reliable in firing performance, the reliability of build-up of the engine can be guaranteed, and the strong ignition time of the igniter can meet the requirements of the engine system.