面向小推力变轨的天文组合自主导航方法  

Integrated Celestial Autonomous Navigation Method for Low Thrust Orbit Maneuver

作　　者：马广富[1] 王伟 张伟[2,3] 黄庆龙[2,3] 彭玉明 张晓[2,3] MA Guang-fu;WANG Wei;ZHANG Wei;HUANG Qing-long;PENG Yu-ming;ZHANG Xiao(Dept.of Control Engineering and Science,Harbin Institute of Technology,Harbin 150001,China;Shanghai Institute of Satellite Engineering,Shanghai 200240,China;Shanghai Key Laboratory of Deep Space Exploration Technology,Shanghai 200240,China)

机构地区：[1]哈尔滨工业大学控制科学与工程系,哈尔滨150001 [2]上海卫星工程研究所,上海200240 [3]上海市深空探测技术重点实验室,上海200240

出　　处：《宇航学报》2020年第9期1166-1174,共9页Journal of Astronautics

摘　　要：针对小行星探测任务对导航系统自主性强、实时性高的需求,研究了一种面向小推力变轨的天文组合自主导航方法。根据工程实践分析并建立了电推进变轨过程中的动力学模型,给出了天文测角测速组合的小行星探测自主导航方案。为克服小行星探测器推力的不确定性,提出了采用自适应交互式多模型无迹卡尔曼滤波(AIMM-UKF)算法,以较少的模型个数实现对导航系统状态的覆盖,克服了模型集合先验信息不准确对导航精度的影响,提高了组合导航系统的鲁棒性和抗干扰能力。最后,通过数学仿真对组合导航算法的性能进行了验证,结果表明本文提出的组合导航方法估计精度更高、计算消耗更小,可满足小行星探测工程任务对导航系统自主性、实时性和高精度的需求。In view of the demand of autonomous and real-time navigation system for an asteroid exploration mission, an integrated celestial autonomous navigation method for low thrust orbit maneuver is studied. Based on the analysis of engineering practice, the dynamic model with electric propulsion during orbit maneuver is established, and the autonomous navigation method combining with astronomical angle and velocity measurement is given. Aiming at overcoming the uncertainty of asteroid probe thrust, an adaptive interactive multi-model unscented Kalman filter(AIMM-UKF) algorithm is proposed to cover the state of the navigation system with several different models, which overcomes the influence of inaccurate prior information of the model set on the navigation accuracy and improves the robustness and anti-disturbance ability of the integrated navigation system. The performance of the algorithm is verified by mathematical simulation. The simulation results show that the presented navigation method is more precise and has less computation than the general UKF algorithm, thus demonstrating the effectiveness of the proposed method, and meeting the demand of autonomous, real-time and high accuracy of the navigation system for asteroid exploration engineering missions.

关 键 词：小行星探测 天文导航 小推力变轨 无迹卡尔曼滤波 测角测速 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]