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本文叙述用于高精度地球指向卫星的姿态测量系统。该系统是以一组捷联式速度积分陀螺仪为基础的,利用精窄缝式星敏感器间断地对恒星进行测量,并将测量结果通过卫星上的卡尔曼滤波器算法,导出姿态和陀螺漂移的估计值去修正系统。介绍了系统部件和卡尔曼滤波器开发的梗概。介绍了系统性能的数字机仿真结果。仿真表明对于766公里轨道高度的卫星,每圈轨道修正14次时,总的姿态误差RMS值(不包括偏置值)为6角秒。仿真表明,系统性能对于每圈轨道上的修正次数以及对卡尔曼滤波器中过量估计被模拟的星敏感器噪音是相当不敏感的。本文叙述所建议的该系统的实验室演示模型。
This article describes attitude measurement systems for high-precision Earth-pointing satellites. The system is based on a set of strapdown speed integrated gyroscopes. The system uses intermittent star sensors to intermittently measure the stars, and then passes the Kalman filter algorithm on the satellite to derive the attitude and the gyro Drift estimate to correct the system. The outline of system components and Kalman filter development is introduced. The numerical simulation results of the system performance are introduced. Simulation shows that for a satellite at orbital altitude of 766 kilometers, the total RMS RMS error value (excluding the offset value) of attitude errors is 6 arc seconds when the orbital correction is 14 times per revolution. Simulation shows that the system performance is quite insensitive to the number of corrections per lap orbit and the star sensor noise that is overestimated in the Kalman filter. This article describes the recommended laboratory demonstration model for this system.