基于红外地平仪的航天器姿态确定技术  

Spacecraft Attitude Determination by Using Infrared Horizon Sensors

作　　者：潘旺华[1] 廖瑛[1] 赵健康[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《计算机仿真》2005年第9期40-43,共4页Computer Simulation

摘　　要：卫星的发展趋向于微小型化,研究小型化、廉价、可靠和中等精度的自主导航系统是非常有必要的。本文提出应用红外地平仪的对地定向航天器姿态确定算法。根据卫星姿态动力学模型建立了基于欧拉角的姿态确定滤波模型。利用地平仪测得的姿态信息,通过卡尔曼滤波器可以确定航天器姿态。进一步提出了姿态确定滤波算法。通过仿真实验,分析比较了模型噪声和测量噪声对定姿精度的影响。仿真算例结果表明,红外地平仪定姿方案可以满足中等姿态精度要求,在对地定向航天器自主导航中具有良好的应用前景。Satellites tend to be micromation in future. It＇s necessary to investigate small, cheap , reliable selfcontained navigation system with moderate precision. An algorithm of attitude determination based on infrared horizon sensors is designed for earth directional spacecraft in this paper. According to the dynamical model of spacecraft＇s attitude, the filter model and algorithm based on euler angle method are presented. Using the data measured by infrared horizon sensors, the attitude of spacecraft can be determined through Kalman filter. After simulation experiments, the effect of plant noise and measurement noise on determination precision is analyzed and compared. The simulation results show that the project of infrared horizon sensors attitude determination has a certain precision, which has an applicable future in the self - contained navigation system of earth directional spacecraft.

关 键 词：红外地平仪 自主导航 卡尔曼滤波器 

分 类 号：V448.22[航空宇航科学与技术—飞行器设计]