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浙江大学学报(工学版)
J4
力学与机械工程     
刚体-附件耦合系统热-动力学稳定性分析
李伟1,薛明德2,向志海2
(1. 清华大学 核能与新能源技术研究院, 北京 100084; 2. 清华大学 工程力学系, 北京 100084)
Thermal-dynamic stability analysis of structural appendages attached to satellite
LI Wei1, XUE Ming-de2, XIANG Zhi-hai2
(1. Institute of Nuclear and New Energy Technology, Tsinghua University, Beijing 100084, China;
2. Department of Engineering Mechanics, Tsinghua University, Beijing 100084, China )
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摘要：

根据卫星的结构特点将之简化为刚体-附件耦合系统.在突加热流作用下,该系统存在两重耦合影响：附件结构的非线性瞬态温度场与舱体刚体转动和附件结构变形之间的相互耦合影响；卫星舱体刚体运动和附件振动之间的相互耦合影响,因此该系统具有高度非线性.针对该耦合系统,以有限元法为研究手段,分析了系统的热诱发振动响应和运动稳定性问题,发展了一套高效、可靠和实用的分析方法.所提出方法的可靠性得到了简单系统理论解的验证,可为卫星系统的设计提供有益的参考.
Abstract:

The satellite was simplified as a coupled system composed of a flexible appendage attached to a rigid body. Under the suddenly applied thermal loading, the system contained two coupling effects, i.e., the coupling effect among the nonlinear transient temperature, the rigid body motion of the hub and the structural deformation of the appendage, and the coupling effect between the motions of the hub and the appendage. So it was a highly nonlinear system. Based on finite element methods (FEM), some efficient, reliable and practical methods were developed to conduct the thermal-dynamic analysis and the corresponding stability analysis for the hub-appendage coupling system. The validity of the presented methods was verified by the existent theoretical solutions. The proposed method can provide beneficial references for the design of satellites．
出版日期: 2009-07-01
:  V414.1  
基金资助:

国家“863”高技术研究发展计划资助项目．
通讯作者: 薛明德,女,教授.     E-mail: xuemd@mail.tsinghua.edu.cn
作者简介: 李伟 (1979-),男,山东文登人,工程师,从事结构弹塑性分析方面的研究.
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引用本文:

李伟, 薛明德, 向志海. 刚体-附件耦合系统热-动力学稳定性分析[J]. J4, 10.3785/j.issn.1008-973X.2009..

LI Wei, XUE Meng-De, XIANG Zhi-Hai. Thermal-dynamic stability analysis of structural appendages attached to satellite. J4, 10.3785/j.issn.1008-973X.2009..

链接本文:

http://www.zjujournals.com/eng/CN/10.3785/j.issn.1008-973X.2009.    或    http://www.zjujournals.com/eng/CN/Y2009/V43/I7/1288

［1］ XUE Ming-de, DING Yong. Two kinds of tube elements for transient thermal-structural analysis of large space structures［J］. International Journal for Numerical Methods in Engineering, 2004, 59: 13351353．
［2］ 程乐锦, 薛明德. 大型空间结构热-动力学耦合有限元分析［J］. 清华大学学报：自然科学版, 2004, 44(5): 681684, 688．
CHENG Le-jin, XUE Ming-de. Coupled thermal-dynamic FEM analysis of large scale space structures ［J］. Journal of Tsinghua University: Science and Technology, 2004, 44(5): 681684, 688.
［3］ JOHNSTON J D, THORNTON E A. Thermally induced attitude dynamics of a spacecraft with a flexible appendage［J］. Journal of Guidance, Control, and Dynamics, 1998, 21(4):581587．
［4］ 薛明德,李伟,向志海. 中心舱体-附件耦合系统热颤振有限元分析［J］. 清华大学学报:自然科学版, 2008, 48(2):270275．
XUE Ming-de, LI Wei, XIANG Zhi-hai. Thermal flutter analysis of a spacecraft with a flexible appendage based on FEM［J］. Journal of Tsinghua University: Science and Technology, 2008, 48(2): 270275.
［5］ LI Wei, XIANG Zhi-hai, CHEN Le-jin, et al. Thermal flutter analysis of large-scale space structures based on finite element method［J］. International Journal for Numerical Methods in Engineering, 2007, 69(5):887907．
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