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为研究星体进行调姿运动时柔性抛物面天线的弹性变形对其视在相位中心的影响,建立了计算抛物面天线动态几何焦点的数学模型,并通过航天器动力学模型对姿态调整过程中天线焦点的动态响应进行数值求解.建立由抛物面天线、太阳帆板和中心星体组成的整星有限元模型,并求出天线无约束边界条件下的固有频率和振型.通过有限元模型和ADAMS联合仿真建立航天器零次刚柔耦合动力学模型并求得姿态调整过程中天线几何焦点的动态响应特性.结果表明,航天器进行姿态调整时,柔性天线面在做大范围整体运动的同时发生弹性振动,使其几何焦点在平衡位置震荡,严重影响星载天线的指向精度.
In order to study the influence of elastic deformation of flexible parabolic antenna on its apparent phase center during the transfer of stars, a mathematical model for calculating the dynamic geometric focus of the parabolic antenna is established. The spacecraft focus in the attitude adjustment process The dynamic response is solved numerically.The whole-body finite element model consisting of a parabolic antenna, a solar panel and a central star is established and the natural frequencies and modes under the unrestricted boundary conditions of the antenna are obtained.The finite element model and the ADAMS co-simulation are established The dynamic response of the spacecraft coupled with zero-order rigid-flexible coupling is obtained and the dynamic response characteristics of the antenna geometrical focal point during the attitude adjustment are obtained. The results show that when the spacecraft performs attitude adjustment, the flexible antenna surface undergoes elastic vibration in a large range of overall motion, So that its geometric focus in the equilibrium position of shock, seriously affecting the accuracy of satellite-based antenna.