摘要
基于极大后验估计原理,提出了一种改进的噪声估计器,以实现对噪声均值和方差的在线估计,抑制滤波器发散。对自适应扩展卡尔曼滤波算法在卫星姿态确定系统中的应用进行了仿真。结果表明新算法滤波精度优于扩展卡尔曼滤波(EKF),与Sage-Husa自适应滤波算法相比,可阻止滤波器发散,提高系统滤波精度。
Based on maximum a posterior （MAP）, a modified noise statistic estimator was proposed in this paper, which was used for compensation the errors by updating mean and covariance of the noise and restraining the filter＇s divergence. The proposed algorithm application in the attitude determination system of satellite was simulated. The results showed that the accuracy of the proposed algorithm was better than that o{ extended Kalman filtering. And it also would keep filter converge and obtain higher accuracy compared with the conventional Sage- Husa filtering.
出处
《上海航天》
2012年第6期21-25,共5页
Aerospace Shanghai
