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提出了一种基于CCD星敏感器的捷联惯性导航系统的空中对准方法。应用双线性方程求解被观测星在星敏感器坐标系中的坐标值及传统最小二乘微分校正法求解捷联惯性导航的姿态,该姿态值与捷联惯性导航解算姿态的差值就是惯性导航系统的失准角。作为Kalman滤波器的观测量,计算机仿真结果表明,天文姿态信息有效地校正了陀螺漂移和初始失准角引起的位置和速度误差。
An air alignment method based on CCD star sensor for strapdown inertial navigation system was proposed. The bilinear equation is used to solve the coordinate of the observed star in the star sensor coordinate system and the traditional least square differential correction method is used to solve the attitude of the strapdown inertial navigation. The difference between this attitude value and the strapdown inertial navigation solution attitude is Misalignment angle of inertial navigation system. As an observation of Kalman filter, computer simulation results show that astronomical attitude information effectively corrects the position and velocity errors caused by gyro drift and initial misalignment angle.