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为了研究空间热载荷对星载天线刚柔耦合多体系统的扰动,根据抛物反射面几何特征,采用壳体单元有限元离散化法,并考虑壳体厚度方向上的温度变化,建立了有限元列式的热传导方程;引入与应变能有关的耦合项,利用拉格朗日法推导了星载天线系统的大范围刚柔耦合动力学方程,研究了温度载荷对星载天线多体系统的动力学特性影响。仿真结果表明:空间热效应引起了动态的温度载荷,与结构变形发生耦合,诱发耦合颤振,加剧柔性反射面的弹性振动,造成卫星姿态和天线指向的扰动,严重影响了星载天线的指向精度。结论对星载天线指向精度的分析与控制具有重要的理论价值及工程实际意义。
In order to study the perturbation of the rigid-flexible coupled multi-body system of the spaceborne antenna, the finite element discretization method based on the geometrical characteristics of the parabolic reflector and the temperature variation in the thickness direction of the shell are used to establish the finite element Based on the Lagrange method, a large range of rigid-flexible coupled dynamic equations of the satellite-based antenna system are deduced. The effects of temperature load on the power of the satellite-carrier multi-body system Learning characteristics affect. The simulation results show that the spatial thermal effect causes dynamic temperature load, which is coupled with the deformation of the structure, induces the coupling flutter, aggravates the elastic vibration of the flexible reflecting surface, and causes the satellite attitude and the antenna pointing disturbance, which seriously affects the pointing accuracy of the spaceborne antenna . Conclusion The analysis and control of pointing accuracy of satellite-based antenna have important theoretical value and practical significance.