基于约束规划的小天体接近段鲁棒制导控制方法  

Robust guidance and control algorithms for small-body proximity operations based on constrained programming

作　　者：高艾[1] 崔平远[1,2] 崔祜涛[1] 

机构地区：[1]哈尔滨工业大学深空探测基础研究中心,黑龙江哈尔滨150001 [2]飞行器动力学与控制教育部重点实验室,北京100081

出　　处：《系统工程与电子技术》2012年第5期989-995,共7页Systems Engineering and Electronics

基　　金：国家高技术研究发展计划(863计划)(2010AA122206)资助课题

摘　　要：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。The robust guidance and control algorithms based on constrained programming for enabling spacecraft proximity operations about small-bodies are developed.Incorporating the gravity models of the target bodies,in addition to enabling the satisfaction of state and control constraints,allows the problem to be cast as a second-order cone program（SOCP）.Considering the influence of uncertainties from gravity model and disturbance on tracking the guidance trajectory,the design of the feedback policy is conducted based on bounding arguments on the model uncertainty.The results from mathematical simulation show that the guidance and control algorithms based on the convex program provide a clear benefit over classical polynomial fit guidance methods in reducing guidance and control deviation and satisfying state and control constraints.

关 键 词：小天体接近 制导与控制 约束规划 二阶圆锥规划 鲁棒反馈控制 

分 类 号：V448.233[航空宇航科学与技术—飞行器设计]