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讨论航天器太阳帆板伸展过程中航天器姿态运动的最优控制问题。利用多体动力学方法导出带太阳帆板航天器姿态运动方程。在系统角动量为零的情况下,带太阳帆板航天器系统的姿态运动控制问题可转化为无漂移系统的非完整运动规划问题。航天器太阳帆板伸展过程控制输入通过样条逼近或曲线拟合确定,并利用粒子群优化算法寻求最优控制输入。该方法克服了以往文献中控制输入在初始和终止时刻不为零的情况。数值仿真表明该方法对航天器太阳帆板展开姿态控制问题是有效的。
The optimal control of spacecraft attitude during spacecraft solar panel extension is discussed. Using Multibody Dynamics Method to Derive Attitude Equation of Spacecraft with Solar Panel. When the system angular momentum is zero, the attitude motion control problem with the solar sail spacecraft system can be transformed into the nonholonomic motion planning problem of drift-free system. Spacecraft solar panel extension process control inputs are determined by spline approximation or curve fitting, and the particle swarm optimization algorithm is used to find the optimal control input. The method overcomes the situation that the control input in the prior literature is not zero at the initial and final moments. Numerical simulation shows that this method is effective in attitude control of spacecraft solar panels.