上海航天
上海航天
상해항천
AEROSPACE SHANGHAI
2012年
6期
21-25
,共5页
Sage—Husa自适应滤波%噪声估计器%非线性滤波%卫星姿态确定系统
Sage—Husa自適應濾波%譟聲估計器%非線性濾波%衛星姿態確定繫統
Sage—Husa자괄응려파%조성고계기%비선성려파%위성자태학정계통
Sage-Husa adaptive filter%Noise statistic estimator%Nonlinear filter%Satellite attitude determination system
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。
基于極大後驗估計原理，提齣瞭一種改進的譟聲估計器，以實現對譟聲均值和方差的在線估計，抑製濾波器髮散。對自適應擴展卡爾曼濾波算法在衛星姿態確定繫統中的應用進行瞭倣真。結果錶明新算法濾波精度優于擴展卡爾曼濾波（EKF），與Sage—Husa自適應濾波算法相比，可阻止濾波器髮散，提高繫統濾波精度。
기우겁대후험고계원리，제출료일충개진적조성고계기，이실현대조성균치화방차적재선고계，억제려파기발산。대자괄응확전잡이만려파산법재위성자태학정계통중적응용진행료방진。결과표명신산법려파정도우우확전잡이만려파（EKF），여Sage—Husa자괄응려파산법상비，가조지려파기발산，제고계통려파정도。
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.
