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针对带挠性帆板航天器简化模型建立了帆板受到突加热流时的拉格朗日能量方程,将帆板的准静态位移分解为空间函数与时间函数的乘积,采用扩展的假定模态法,推导了系统的动力学方程.指出温度差是引起姿态变化的扰动源,分析了热时间常数及温度差等参数对姿态的影响.从频域出发,分析热引起的扰动力矩对航天器姿态控制系统的影响.数值仿真结果验证了分析的正确性.
For the simplified model of a flexible sailboard with spacecraft, the Lagrange energy equation of the sailboard subjected to sudden heat flow is established. The quasi-static displacement of the sailboard is decomposed into the product of space function and time function, and the extended assumed mode Method is used to derive the kinetic equation of the system. The temperature difference is the disturbance source that causes the attitude change. The influence of the parameters such as the thermal time constant and the temperature difference on the attitude is analyzed. Starting from the frequency domain, Attitude control system.The numerical simulation results verify the correctness of the analysis.