基于地平仪两轴姿态测量的卫星自主相对导航  

Autonomous relative navigation with two-axis attitude measurements using only infrared earth sensor

作　　者：任家栋[1,2,3] 曾庆双[1] 朱虹 丰保民 

机构地区：[1]哈尔滨工业大学航天学院,哈尔滨150001 [2]上海航天控制技术研究所,上海201109 [3]上海市空间智能重点实验室,上海201109

出　　处：《中国惯性技术学报》2015年第5期597-601,606,共6页Journal of Chinese Inertial Technology

基　　金：国家高技术研究发展计划项目(2014AA8091073)

摘　　要：针对近圆轨道编队卫星,提出了一种仅需要地平仪两轴姿态测量的卫星自主相对导航滤波方法,利用星间相对测量与偏航姿态运动的弱相关性,解决了欠偏航量测下的相对位置估计以及三轴姿态确定问题。可观性分析证明了该方法的可行性及对编队构型参数的适应性。大量仿真表明,对于绕飞和伴飞构型,该方法均收敛,性能特性与理论分析一致。针对当前典型的地平仪与星间测量能力,相对位置滤波精度均优于2 m(3σ),绕飞构型偏航姿态精度优于1.0°(3σ),伴飞构型偏航姿态精度优于0.5°(3σ),是对中等精度编队卫星配置简化的有益探索。An autonomous relative navigation method is presented for satellite formations on near circular orbit,which need only IRES（Infra Red Earth Sensor） attitude sensor and necessary inter-satellite tracking sensor. By using the existing poor relation between relative position measure and yaw attitude motion,the problem of estimating relative motion state and three-axis attitude when with loss yaw attitude information is solved. Observability analysis proves the method＇s feasibility and adaptability. Simulation results indicate that the algorithm is convergent for both the fly-around and the companying formation configuration,which are consistent with the theoretical conclusion. Based on the current staple IRES and inter-satellite measure sensor,the relative position estimation error is 2 m（3σ）,yaw attitude estimation error is 1.0°（3σ） for fly-around formation,and 0.5°（3σ） for accompany flight formation,which means that the method is a beneficial approach to simplify the spaceborne apparatus for medium-precision flying formation.

关 键 词：编队飞行 滤波 相对导航 自主 可观性 

分 类 号：V448.21[航空宇航科学与技术—飞行器设计]