基于矢量观测确定卫星轨道姿态:欧拉角估计器

Determination of satellite orbital attitude from vector observation: Euler-angle estimator

针对“矢量观测+陀螺”这种典型的三轴稳定卫星姿态确定系统配置模式,采用欧拉角作为姿态参数,应用扩展卡尔曼滤波技术综合处理姿态测量信息,给出了具有良好滤波性能的轨道姿态估计算法。在算法的设计过程中,针对单矢量观测情况,通过改进协方差修正算法加快了状态估值的收敛速度;针对多矢量观测情况,把QUEST法作为矢量观测数据压缩技术有效地结合进姿态估计器中,使得在多矢量观测情况下的滤波修正算法得到了简化。

An extended Kalman filter algorithm has been developed for determining the three-axis stabilized satellite orbital attitude by Euler angles using the measurements from the typical attitude measurement system composed of vector observations and gyros. During the development of the filtering algorithm, a modified method is proposed for updating the estimated error covariance matrix in the case of one vector observation used to quicken the convergent rate of state estimates. In addition, the QUEST algorithm is efficiently combined into the orbital attitude estimator as a compressing technique for multi-vector observation information to simplify the update implementation. Both efficiency and good performance of the satellite orbital attitude estimator are demonstrated through Monte-Carlo simulations.