论文部分内容阅读
以小天体接近段任务为背景,提出了一种基于约束规划的鲁棒制导控制方法。该方法将目标天体引力模型引入轨迹规划过程中,并将具有控制约束与轨迹状态约束的非线性动力学路径规划问题转化为以优化燃耗为性能指标的二阶圆锥规划(second-order cone program,SOCP)问题;同时考虑目标天体引力模型与外界干扰等不确定因素对轨迹跟踪的影响,基于模型不确定界设计鲁棒反馈控制律。数学仿真证明,在相同条件下,基于凸规划的制导控制性能无论在制导控制偏差或是状态与控制约束满足方面均优于传统多项式拟合制导控制算法。
Based on the mission of small celestial bodies, a robust guidance control method based on constrained programming is proposed. In this method, the target celestial body gravity model is introduced into the trajectory planning process, and the nonlinear dynamic path planning problem with control constraints and trajectory state constraints is transformed into the second-order cone program with optimized fuel consumption as the performance index , SOCP). At the same time, the influence of uncertainties such as target celestial body gravitation model and external disturbance on trajectory tracking is considered, and robust feedback control law is designed based on model uncertainty. Mathematical simulation proves that under the same conditions, the guidance control performance based on convex programming is superior to the traditional polynomial fitting guidance control algorithm in terms of guidance control deviation or state and control constraint satisfaction.