摘要
利用高超声速冲压发动机燃烧室结构试验结果完成了地面试验状态下燃烧室壳体复杂结构随机振动响应分析,并与试验结果进行了对比分析,试验验证了所采用的飞行器复杂结构随机振动响应分析方法和技术途径.在此基础上,采用试验压力载荷数据,对飞行状态下燃烧室结构的随机振动响应进行了分析,得到燃烧室结构加速度响应的功率谱密度曲线及均方根值,该项工作对飞行器的动力环境初步预示工作具有重要的工程应用价值.
The testing results of combustion chamber structure of hypersonic ramjet were used, which finished the analysis to structure random vibration response of combustion chamber shell. Meanwhile, both of them were compared ,which gave us a satisfied consequence. The analysis and technology method of random vibration response of vehicle complex structure were verified by this test. On the basis of that by taking advantage of pressure load data and analysising the random vibration response of combustor chamber in flight regime, the RMS（Root Mean Square） and PSD （Power Spectral Density） of acceleration response were presen- ted, which was very important to the work of preliminary of dynamic environment of fight vehicle.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2008年第8期981-985,共5页
Journal of Beijing University of Aeronautics and Astronautics
基金
教育部新世纪优秀人才支持计划资助项目(NCET-06-0171)
