【作者】 王捷；

【导师】 刘锦阳；

【作者基本信息】 上海交通大学 ， 一般力学， 2012， 硕士

【摘要】 考虑热效应的刚-柔-热耦合的动力学问题具有一定的工程应用背景。在机械制造、航空、航天等众多领域中。在瞬时热载荷的作用下，柔性部件会产生热变形，由于姿态运动和变形的相互耦合作用，热变形还会对姿态运动产生影响。此外，在热载荷作用下，热变形和姿态角的改变对温度场辐射角的影响也不可忽略，必须同时考虑刚体运动、弹性变形和温度场的耦合，因此，考虑热效应的刚-柔-热耦合动力学问题越来越受到工程界的重视，建立精确的有限元模型对于柔性体的刚柔耦合动力学理论的发展和工程实际问题的解决具有重要意义。本文研究柔性多体系统刚-柔-热耦合动力学特性。以三种航天器为研究对象，基于柔性多体系统动力学理论，考虑了柔性附件弹性变形和姿态角的改变引起的热辐射边界条件的变化，建立了中心刚体和柔性附件多体系统的刚-柔-热耦合的动力学方程。通过对热载荷作用下航天器多体系统的数值仿真研究了各特征参数对于柔性多体系统动力学特性的影响，揭示了引起热颤振和热失稳的根本原因。第一章对刚-柔耦合动力学和热耦合动力学的前人工作进行总结，提出了本论文的研究目标。第二章对哈勃天文望远镜的多体系统的刚-柔-热耦合特性进行研究。基于柔性多体系统动力学理论，考虑了柔性附件弹性变形引起的热辐射边界条件的变化，建立了中心刚体和太阳能毯柔性附件多体系统的刚-柔-热耦合的动力学方程。通过对热载荷作用下哈勃天文望远镜多体系统的数值仿真研究了各特征参数对于柔性附件热颤振的影响。第三章对卫星和太阳帆板多体系统的刚-柔-热耦合动力学进行研究。考虑热辐射强度与卫星姿态角和帆板角变形的耦合关系，建立了热传导变分方程，用虚功原理建立了卫星和太阳帆板的动力学变分方程，用有限单元法离散，建立刚-柔-热耦合的多体系统的动力学方程。通过热载荷作用下卫星-帆板多体系统的数值仿真研究刚-柔-热耦合特性，揭示了热颤振和高速转动时系统失稳的根本原因。第四章对热辐射作用下旋转航天器和柔性天线的刚-柔-热耦合动力学性质进行研究。在建立刚-柔-热耦合动力学模型的基础上，综合研究热辐射角、阻尼系数和角速度对热颤振和系统失稳的影响，得到稳定范围。第五章对全文的研究工作进行总结。更多还原

【Abstract】 Dynamics problems considering the thermally induced rigid-flexible-thermal coupling have great application in certain engineering background,such as mechanical manufacturing, aviation, aerospace and many otherfields. Applied with thermal load, the thermal deformation is induced,which has significant influence on the rotational motion of the wholemechanism system after a period of time. Concerning thermal load, theinfluence of the deformation and the change of the rotational angle uponthe temperature field radiation angle cannot be neglected, therefore thecoupling effect of rigid body movement, elastic deformation andtemperature field should be considered. In the recent years, therigid-flexible-thermal coupling problems of the spacecraft appendageshave been paid attention to. It is important to establish a more accuratefinite element model for solving the rigid-flexible-thermal couplingproblems in engineering application. In this paper, rigid-flexible-thermalcoupling dynamic performance of flexible multibody system was investigated. Based on the theory of flexible multibody system, therigid-flexible-thermal coupling dynamic equations of three spacecraftmultibody systems were derived considering the change of the thermalboundary condition caused by elastic deformation and the change of therotational angle. Simulation of the spacecraft system applied with thermalload was used to investigate the effect of the characterized parameters onthe dynamic performance of the flexible multibody system. The mainfactors that induce the thermal fluttering and instability are analyzed.In chapter one, the previous work on rigid-flexible coupling dynamicsand thermoelatic dynamics is reviewed, and the objective of thedissertation is proposed.In chapter two, rigid-flexible-thermal coupling dynamic performanceof the Hubble Space Telescope (HST) is investigated. Based on the theoryof flexible multibody system, the rigid-flexible-thermal coupling dynamicequations of multibody system composed of the central rigid body andflexible blanket are derived considering the change of the thermalboundary condition caused by the elastic deformation. Simulation of theHubble Space Telescope applied with thermal load is used to investigatethe effect of the characterized parameters on the thermal flutter of theflexible appendages. In chapter three, the rigid-flexible-thermal coupling dynamics of thesatellite and plate multibody system is investigated. Considering thecoupling relation between the heat flux of radiation and the rotationalangle of the satellite as well as the rotational deformation of the plate, thevariational heat conduction equations are derived. Based on virtual workprinciple, the variational dynamic equations of the satellite and platemultibody system are derived. By leading into the kinematics constraintequations and using finite element method, the rigid-flexible-thermalcoupling dynamic equations of the flexible multibody system areestablished. Furthermore, the main factors that induce the fluttering andstability of the dynamic system are analyzed.In chapter four, the rigid-flexible-thermal coupling dynamicperformance of the rotating satellite and antenna multibody system isinvestigated. The influence of the radiation angle, damping coefficient andthe angular velocity on the fluttering and instability of the system isinvestigated, and the stability region is calculated.In chapter five, the research work is summarized and the conclusion isobtained.更多还原