摘要
航天器部件因热诱发的弯扭耦合振动会发生破坏。为了解热诱发弯扭耦合振动的机理,发展了一种14个自由度的二节点开口薄壁梁单元。该单元综合考虑了翘曲、预应力与热应变的影响,得到特有的质量阵、刚度阵和载荷阵。与其他类型梁单元组集后,通过模态分析的方法,得到整个结构的动力学响应。对Hubble太空望远镜的太阳能帆板,用该方法求得的固有频率和固有振型的数值解与近似理论解符合甚好。该分析解释了热使太阳能帆板发生扭转破坏的原因。
The failure of space structures caused by thermally induced vibrations of satellite appendages is a very important problem for space structure designs, but the cause of thermally induced torsional vibrations is still unknown. This paper describes a two node thin-walled open section beam element with 14 degrees of freedom used to analyze the torsional vibrations. The mass, stiffness, and load matrices can model warping, prestressing forces, and thermal strains. The thermal-dynamic response of the structure was obtained using the modal analysis method. Characteristic values for the solar arrays on the Hubble Space Telescope agree well with the approximatel theoretical solution. The cause of the torsional vibrations of the Hubble solar arrays is explained by the thermal-dynamic analysis.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2005年第2期262-266,共5页
Journal of Tsinghua University(Science and Technology)
基金
国家"八六三"高技术项目(863-2-2-1-9)
关键词
航天器结构力学
太阳能帆板
开口薄壁杆
热诱发振动
有限单元法
space structure mechanics
solar array
thin-walled open section beam
thermally induced vibration
finite element method
