基于多项式插值的太阳帆板展开最优控制

Optimal control of stretching process of solar array on spacecraft based on polynomial interpolation method

建立了航天器太阳帆板展开运动模型,运用高阶多项式插值方法逼近太阳帆板关节运动轨迹,将太阳帆板关节铰耗散能作为目标函数,将插值多项式的系数作为优化参数,采用序列二次规划法(SQP)优化求解了关节运动轨迹曲线。数值仿真结果表明:航天器本体和太阳帆板从初始位置到终端位置的过程中,能准确到达目标位形,轨迹平滑连续,没有迂回运动,保证了系统展开过程的平稳性;控制输入变化幅度较小,且始末时刻控制输入均为零,验证了本文方法的有效性。

The main purpose of the present research is to study the optimal control of the deployment process of spacecraft solar panels. When the spacecraft with solar panels is not affected by external momentum, the momentum moment of the system is conserved relative to the total center of mass, and the deployment of the solar panels is a non-holonomic motion. The polynomial interpolation is used to approximate the joint motion of solar panels, and the nonholonomic motion planning problem is transformed into the optimal control problem of the deployment process of solar panels. Firstly, the deployment model of spacecraft solar panels is established. The high-order polynomial interpolation method is used to approximate the joint trajectory of solar panels. The dissipated energy of solar panels is taken as the objective function, and the coefficient of interpolation polynomial is taken as the optimization parameter. Sequential quadratic programming(SQP) is used to optimize the joint trajectory curve. Numerical simulation results obtained show that the spacecraft body and solar panels can reach the target configuration accurately from the initial position to the terminal position, the trajectory is smooth and continuous, and there is no circuitous movement, which ensures the stability of the system deployment process. The change range of the control input is small, and the control input is zero at the beginning and the end. The validity of the proposed method is verified.