The optimization method of a mathematical model and connected-pipe experimental technique for a test in altitude test facility (ATF) of a liquid fuel ramjet engine was researched.The optimization of the simple mathema...The optimization method of a mathematical model and connected-pipe experimental technique for a test in altitude test facility (ATF) of a liquid fuel ramjet engine was researched.The optimization of the simple mathematical model was divided into two steps.Firstly,using the test engine's geometry configuration size data,a preliminary adjustment was done.Secondly,using experimental test data,the components' experiential coefficients were modified appropriately.Emphasis was laid on the simulation technique of flight condition and parameters measurement method.The experimental technique was applied to a ramjet ATF test successfully.The comparison results show that the optimized-model has higher precision and the nozzle gross thrust difference drops from 12% to about 4%.展开更多
利用某冲压发动机直连试车试验力学环境测量结果,分析总结了冲压发动机的噪声、振动以及冲击等环境特点和规律,并与常规固体发动机进行了对比,最后与飞行振动环境进行了天地相关性分析,印证了DEF STAN 00-35标准中"强烈建议必须根...利用某冲压发动机直连试车试验力学环境测量结果,分析总结了冲压发动机的噪声、振动以及冲击等环境特点和规律,并与常规固体发动机进行了对比,最后与飞行振动环境进行了天地相关性分析,印证了DEF STAN 00-35标准中"强烈建议必须根据飞行测量结果确定冲压导弹的振动试验条件"的结论,可为冲压飞行器的力学环境设计提供参考。展开更多
文摘The optimization method of a mathematical model and connected-pipe experimental technique for a test in altitude test facility (ATF) of a liquid fuel ramjet engine was researched.The optimization of the simple mathematical model was divided into two steps.Firstly,using the test engine's geometry configuration size data,a preliminary adjustment was done.Secondly,using experimental test data,the components' experiential coefficients were modified appropriately.Emphasis was laid on the simulation technique of flight condition and parameters measurement method.The experimental technique was applied to a ramjet ATF test successfully.The comparison results show that the optimized-model has higher precision and the nozzle gross thrust difference drops from 12% to about 4%.
文摘利用某冲压发动机直连试车试验力学环境测量结果,分析总结了冲压发动机的噪声、振动以及冲击等环境特点和规律,并与常规固体发动机进行了对比,最后与飞行振动环境进行了天地相关性分析,印证了DEF STAN 00-35标准中"强烈建议必须根据飞行测量结果确定冲压导弹的振动试验条件"的结论,可为冲压飞行器的力学环境设计提供参考。
