卫星姿态测量信息的卡尔曼滤波技术研究  

Research on Kalman Filter Technology for Measurement Information of Satellite Attitude

作　　者：田蔚风[1,2] 金志华[1,2] 施红兵[1,2] 陆恺[1,2] 姜金奎[1,2] 方芳[1,2] 彭仁军[1,2] 

机构地区：[1]上海交通大学 [2]上海航天局812研究所

出　　处：《中国惯性技术学报》1998年第4期19-24,共6页Journal of Chinese Inertial Technology

基　　金：国防科工委基金

摘　　要：本文在研究由陀螺仪、红外地球敏感器和太阳敏感器组成的卫星姿态测量系统的基础上，应用了改进的卡尔曼滤波算法进行信息处理，克服了卡尔曼滤波器的发散现象。本文还提出了限定增益系数的方法，以抑制俯仰角过大的估计误差。本文设计的卡尔曼滤波器适用于对地观测卫星的测量系统，能获取较低噪声的姿态测量信息。Based on research for measuring system of satellite attitude which consists of gyroscopes,infrared earth sensors and solar sensors,a modified Kalman filtering algorithm is presented in this paper,which can restrain error divergence caused by Kalman filter.A method to limit the amplification in a certain range is proposed for restricting the big estimated error of pitch attitude angle.The Kalman filter is suitable to the measuring system of a remote sensing satellite,by which an attitude measurement information with lower noise can be obtained.

关 键 词：卫星姿态 测量系统 卡尔曼滤波 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]