空间控制技术与应用 ›› 2013, Vol. 39 ›› Issue (1): 34-39.doi: 10.3969/j.issn.1674-1579.2013.01.006
摘要： 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.
Abstract：With the sudden temperature change of the solar panels considered, Lagrange’s energy equation of the system is established. The quasistatic bending is factorized into two types of functions: one is the shape function and the other is time function. Using the extended assumed modal method, the system dynamics model is derived. Analytical results demonstrate that temperature difference results in the attitude error. And the effects of thermal time constant and temperature difference on the attitude dynamics of the vehicle are studied. In the frequency domain, the effect of thermally induced disturbance torque on the spacecraft attitude control system is analyzed. Finally numerical simulations are provided to verify the correctness of the analysis.
