摘要
针对大型空间结构的热诱发振动问题,发展了一种热动力学耦合的有限元方法。将结构变形对入射热流的影响进行Taylor展开并略去高阶项,从而得到耦合结构变形的热传导方程,由振型叠加法得到减缩并解耦的动力学方程,然后通过时间积分方法混合迭代求解结构的热动力学响应。对哈勃太空望远镜太阳能帆板的热颤振行为,该方法所得数值解与文献理论解符合得较好。对复杂的空间结构给出了热动力学响应,并发现热动力学耦合效应和热诱发振动稳定性的决定因素是结构参数及加热条件。
Thermally induced vibration of large space structures was analyzed using a coupled thermal-dynamic finite element method (FEM). The heat conduction equations were coupled with the structural deformations by expanding the heat generation terms in terms of powers of the deformations in Taylor series and neglecting higher-order items. Reduced, uncoupled motion equations were then obtained by modal superposition. The thermal-dynamic response of the space structures was determined by solving these equations with an iterative time integration method. Numerical results for the thermal flutter of the solar array on the Hubble Space Telescope agree well with the analytical solution. The thermal-dynamic responses for a typical complex space structure were analyzed. The result shows that the structural properties and heating conditions play a decisive role in the thermal-dynamic coupling and thermally induced vibration stability.
出处
《清华大学学报（自然科学版）》
EI
CAS
CSCD
北大核心
2004年第5期681-684,688,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)
