基于改进线性二次型调节器的近地轨道编队卫星鲁棒控制

摘要

In order to solve the configuration divergence problems of formation satellites under the complex mechanics environment in near-earth space,especially under the non-spherical perturbation influence,a formation satellites configuration control method based on improved LQR (linear quadratic regulator)was presented.The method estimated the maximum bounded range of error caused by an un-modeled perturbative force in near-earth space formation satellites configuration design,then used the 2-norm of maximum bounded range to improve the classical LQR method and improved the robustness of classical LQR controller in controlling formation satellites configuration.In order to evaluate the effectiveness of improved method,a quantitative criterion for judging the robustness was given.The simulation results show that the improved method can greatly improve the robustness of classical LQR method and improve the resistance ability of formation satellites control methods for all kinds of uncertainty.%为解决编队卫星在近地空间复杂力学环境特别是地球非球形摄动作用下构型易发散的问题，给出一种基于改进线性二次型调节器的编队卫星构型控制方法。该方法先估计近地空间编队卫星构型设计时由未建模摄动力引起的误差最大有界范围，再利用误差最大有界范围的二范数改进经典的线性二次型调节器控制方法，提高经典线性二次型调节器控制器在控制编队卫星构型时的鲁棒性。为评价改进方法的有效性，给出了一种鲁棒性强弱的量化评判标准。仿真结果表明，改进的方法可以大大提高经典线性二次型调节器方法的鲁棒性，增强编队卫星控制方法对各种不确定项的抵御能力。