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航天器柔性附件在突加太阳辐射热载荷作用下的热诱发振动会严重影响航天器的正常工作。航天器是典型的多体系统;部件间的相互作用会严重影响航天器的热诱发振动响应,因而有必要使用多体系统动力学的方法对此进行研究。该文在柔性多体系统动力学框架内,推导建立了一种考虑辐射换热的热-结构耦合圆管单元。温度变化会使圆管单元产生轴向伸缩和横向弯曲;同时,在给定辐射热流作用下,圆管单元受热条件与其姿态和变形相关。使用该圆管单元、刚体单元和柔性体单元可以实现多体系统动力学热-结构耦合分析。该文的方法首先用于哈勃太空望远镜太阳能电池板简化模型的热诱发振动分析,所得结果与文献结果吻合良好。然后,该文研究了由本体、动量轮、柔性支撑杆和端部质量组成的航天器在突加辐射热流作用下的振动响应。结果表明:各部件间的相互作用会对航天器的热诱发振动响应产生显著影响。
The heat-induced vibration of spacecraft flexible attachments under the sudden solar radiation heat load will seriously affect the normal operation of the spacecraft. The spacecraft is a typical multi-body system. The interaction between components can seriously affect the heat-induced vibration response of the spacecraft. Therefore, it is necessary to study it using multi-body system dynamics. In the framework of flexible multi-body system dynamics, a thermo-structural coupled circular tube unit considering radiation heat transfer is derived. The temperature change will cause the axial expansion and the horizontal bending of the circular pipe unit. Meanwhile, under the given radiant heat flow, the heating conditions of the circular pipe unit are related to its attitude and deformation. The multi-body system dynamics thermo-structural coupling analysis can be realized by using the tube unit, the rigid body unit and the flexible body unit. The method of this paper is firstly applied to the thermal induced vibration analysis of a simplified model of the solar panel of the Hubble Space Telescope. The obtained results are in good agreement with the literature results. Then, the paper studies the vibration response of a spacecraft consisting of body, momentum wheel, flexible support rod and end mass under sudden radiant heat flow. The results show that the interaction between the components will have a significant impact on the thermally induced vibration response of the spacecraft.