Performance evaluation of star sensor low frequency error calibration

Multiple-model adaptive estimator for spacecraft attitude sensor calibration

“…However, when the LFE occurs, the KF suffers from a performance loss due to the LFE effect in the measurements and consequently in the residuals of the filter. To cope with the unfavorable effect of the star sensor LFE, a calibration method based on the AKF is presented by Xiong et al (2014) based on the framework for the attitude determination KF. The LFE parameters a x , b x , a y , b y , a z and b z are included in the dynamic model, such that the AKF can be used to estimate the LFE parameters as well as the attitude.…”

“…In the case that the LFE does not occur (or the magnitude of the LFE is sufficiently small), the calibration error may distort the attitude estimate distinctly, and the AKF may be even worse than the KF. It is recommended by Xiong et al (2014) that the LFE calibration method based on the AKF should be used in the case that the magnitude of the LFE is rather large. However, before the launch of the spacecraft, the magnitude of the star sensor LFE is uncertain for the designers of the spacecraft attitude control system.…”

“…Recently, a Fourier series has been utilized to describe the LFE, and an augmented Kalman filter (AKF) is developed by Xiong et al (2014) to estimate the parameters of the Fourier series. The attitude determination accuracy can be improved by using the calibration algorithm based on the AKF in the presence of the LFE.…”

Autonomous relative navigation error compensation method for small body exploration based on sequence-images

“…目前, 国内外研究学者大多采用多敏感器互补、 误差影响函数等方法实现误差补偿. Armellin等人 [11] 在仅获得测角信息的情况下, 在初始轨道确定中利用 泰勒微分代数将误差从观测空间映射到状态空间, 通 过计算误差数据的均值和协方差实现误差补偿; 张春 青等人 [12] 基于线性时变系统的可观测性理论将未知 系统偏差作为待估参数, 通过自校准滤波实现误差补 偿; Abdelrahman和Park [13] 在航天器姿态动力学的基础 上, 利用磁强计和光纤陀螺仪测量数据实现了误差补 偿; Chang等人 [14] 采用姿态数据库校准敏感器测量误 差; Wang等人 [15] 提出了一种光学敏感器的在轨分布标 定方法, 该方法可在外部参数标定的广义相机框架下, 实现内部参数标定; 熊凯等人 [16][17][18]…”

Vertical Accuracy Simulation of Stereo Mapping Using a Small Matrix Charge-Coupled Device

“…The main elements that reduce the relative accuracy of attitude are (1) random error, such as the noise resulting from attitude measurement equipment (e.g., star sensor noise and gyro noise); (2) attitude high-frequency error, such as high-frequency jitter of the platform (e.g., that caused by momentum wheel activities) [27]; (3) attitude low-frequency drift, such as angle change between the CCD camera and star sensor caused by drift of the star sensor's optic axis or by on-orbit thermal environment change. The third factor has the greatest influence when GCPs are not used [28][29][30][31].…”