星敏感器安装误差标定技术研究

星敏感器是一类具有自主高精度姿态测量能力的仪器,输出姿态精度可达到角秒级。但实际组合导航应用中,星敏感器安装误差往往可达角分级,远远大于仪器本身误差,影响其使用品质,因此有必要在使用前对星敏感器安装误差进行建模标定。研究发现,星敏感器安装误差与惯导姿态误差存在耦合关系,难于分离。设计了一种快速标定方法,利用惯导输出姿态、位置信息以及星敏感器姿态输出构造观测量,建立卡尔曼滤波模型,通过滤波估计实现安装误差的地面标定。仿真结果表明,载体需要进行2个轴向上的机动才能将星敏感器三轴安装误差估计出来。相较于依靠外部基准姿态进行标定的方案,本方法具有快速高效、可操作性强等优点。

Research on Calibration Technology of Star Sensor Installation Error Angle

The star sensor is a kind of instrument with autonomous high precision attitude measurement ability, whose output attitude accuracy can reach the arc-second level. However, the installation error angle of the star sensor often reaches the arc-minute level in the practical navigation applications. This error is far greater than the instrument error, which restricts its quality of measurement. Therefore, it is necessary to model and calibrate the installation error angle. In this study, it suggests that there is an inseparable coupling relationship between the installation error angle and the inertial attitude error. This paper proposes an installation error angle calibrating method using the attitude, the position of inertial navigation system and the star sensor''s attitude to establish observed information and a Kalman filter model is used to fast calibrate the installation error angle on the ground. The simulation results show that the carrier needs two axial attitude maneuvers to estimate the three-axis installation error angle of the star sensor. Compared with the method of calibrating by external reference attitude, the proposed method is faster, more efficient, and of stronger operability.