条带式太阳帆航天器的热致结构动力学响应

本文研究条带式太阳帆在近地轨道运行进出地球阴影时的热致结构动力学响应，建立了在太阳热辐射和光压共同作用下的太阳帆结构动力学方程，采用分布传递函数法，给出了条带式太阳帆热致结构稳态振动幅频响应的计算方法。算例结果表明：热辐射冲击是引起近地轨道太阳帆结构动力学响应的主要原因，光压引起的结构响应可忽略不计；增加桅杆壁厚不能有效抑制太阳帆的热致结构动态响应；增大阻尼，减小结构的热膨胀系数能够明显减小太阳帆热致结构响应的振幅；热致结构动态响应是设计大尺寸近地轨道太阳帆必须解决的问题。本文提出的方法可为太阳帆结构设计、姿态和轨道控制提供有力的分析工具。

Thermally Induced Structural Dynamic Response of a Stripped Solar Sail Spacecraft

The thermally induced structural dynamic response of a stripped solar sail orbiting in low Earth orbit is studied in this paper. Considering the combined effect of solar radiation pressure and solar heat flux, the thermal structural dynamic equations of the stripped solar sail are derived. By using the distributed transfer function method, the analytical method to calculate the amplitude frequency responses of the stripped solar sail is presented. The numerical results demonstrate that the sudden change of solar heat flux produces obvious structural dynamic response while the structural dynamic response caused by solar radiation pressure is negligible; increasing thickness of the boom cannot suppress the thermally induced structural dynamic response of the stripped solar sail; increasing damping and decreasing thermal expansion can suppress the thermally induced structural dynamic response of the stripped solar sail efficiently; and the thermally induced structural dynamic response should be appraised in designing a large solar sail in low Earth orbit. This presented method provides an efficient analysis tool for designing and controlling the stripped solar sail.