一种小卫星高精度自主定轨/定姿一体化新方法  

New method for high-precision autonomous determination of integrated orbit/attitude of small satellite

作　　者：王鹏[1,2] 张迎春[3] 

机构地区：[1]东南大学仪器科学与工程学院,南京210096 [2]东南大学微惯性仪表与先进导航技术教育部重点实验室,南京210096 [3]哈尔滨工业大学航天学院,哈尔滨150001

出　　处：《中国惯性技术学报》2014年第6期741-747,754,共8页Journal of Chinese Inertial Technology

基　　金：江苏省自然科学基金(BK20130636);中国航天科技集团公司卫星应用研究院创新基金项目(2012-1510);东南大学微惯性仪表与先进导航技术教育部重点实验室开放基金项目(201211)

摘　　要：基于传统小卫星对轨道和姿态参数确定采用分别计算的复杂模式,提出了一种利用地磁场和天文信息同时确定卫星轨道和姿态参数的新方法。首先通过分析小卫星轨道动力学J2模型和卫星姿态动力学模型,建立系统状态方程。其次将三轴磁强计与地磁场模型参考值的矢量作差,分析微分差值与状态变量的数学关系,建立定位/定姿观测方程。利用星敏感器提供的高精度姿态信息,建立定姿观测方程,同时利用星敏感器间接敏感地平观测折射恒星,建立定位观测方程。最后提出基于信息融合的先进滤波算法,并通过对多种导航模式进行数值仿真及结果分析,论证所设计一体化方法提高了系统定轨/定姿的精度和可靠性。A new method for simultaneously determining the orbit and attitude of satellite based on three-axis-magnetometer (TAM) and celestial data is presented, which is a breakthrough over traditional pattern of separately treating the satellite's orbit and attitude. Firstly, the system state equation is established by analyzing the satellite orbit dynamics J2 model and deducing the satellite attitude dynamics model. By utilizing the differences between the measured and computed magnetic field components, a set of measurement equation is established. By utilizing the attitude information and indirect sensing horizon from star sensor, another group of measurement equations are established. The autonomous navigation method and algorithm are designed and simulated. The results of computer simulation show that the proposed system improves the navigation precision and reliability. ©, 2014, Editorial Department of Journal of Chinese Inertial Technology. All right reserved.

关 键 词：三轴磁强计 天文导航 轨道姿态一体化 信息融合 

分 类 号：V448.2[航空宇航科学与技术—飞行器设计]