论文部分内容阅读
为了研究液体推进剂消耗对某大型卫星结构动特性的影响,采用简化的“弹簧-质量”模型分析了推进剂消耗对结构动特性的影响趋势;基于MSC.PATRAN/NASTRAN给出了动力学分析过程中液体推进剂的等效建模和分析方法,包括梁单元法、附加质量法、“RBE3-质量点”单元法和虚拟质量法等;建立了该卫星结构的有限元模型,进行了结构动力学特性和动响应分析,讨论了液体推进剂消耗对其动特性的影响规律。研究结果表明:随着推进剂的消耗,卫星整体振型的固有频率逐渐增大,而部分局部振型的固有频率保持不变;随着推进剂的消耗,卫星仪器安装板动力学响应峰值逐渐增大,所对应的频率也逐渐增大。
In order to study the influence of liquid propellant consumption on the dynamic characteristics of a large satellite structure, the simplified “spring-mass” model was used to analyze the influence of propellant consumption on the dynamic characteristics of the structure. Power was given based on MSC.PATRAN / NASTRAN The equivalent modeling and analysis methods of liquid propellants in the course of the analysis include beam element method, additional mass method, RBE3-mass point method and virtual mass method. The finite element model , The dynamic characteristics and dynamic response of the structure were analyzed. The influence of liquid propellant consumption on its dynamic characteristics was discussed. The results show that with the consumption of propellant, the natural frequency of the satellite’s overall mode gradually increases while the natural frequency of some local modes remains unchanged. With the consumption of propellant, the dynamic response peak of the satellite instrument mounting plate gradually increases Increase, the corresponding frequency is also gradually increased.