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CN106767767A 一种微纳多模星敏感器系统及其数据融合方法 无效 - 驳回

一种微纳多模星敏感器系统及其数据融合方法
摘要：
本发明提供一种微纳多模星敏感器系统，包括：陀螺以及卡尔曼滤波器，均安装在星敏感器内形成单机系统。本发明还提供一种微纳多模星敏感器系统的数据融合方法，包括：利用陀螺和星敏感器的测量数据同时实现对姿态和陀螺常值漂移的估计，并保存；利用陀螺常值漂移的估计值，对卫星姿态估计的误差进行修正，得到更精确的姿态和姿态角速度。本发明提供的微纳多模星敏感器系统，体积小，可靠性高，制造成本低，对卫星姿态能够实时修正。本发明提供的微纳多模星敏感器系统的数据融合方法，使陀螺测量的角速度精度更高，使星敏感器能够输出更高的姿态数据，提高了卫星姿态修正的精度。
摘要（英）：

The invention provides a micro-nano multimode star sensor system which comprises a gyro and a kalman filter which are arranged in a star sensor so as to form a stand-alone system. The invention further provides a data fusion method for the micro-nano multimode star sensor system. The method comprises the following steps: simultaneously estimating theattitude and gyro constant drift by utilizing the measured data of the gyro and the kalman filter, and saving the posture and gyro constant drift; and correcting a satellite attitude estimation error by utilizing the estimated value of the gyro constant drift, thereby obtaining accurate attitude and attitude angular velocity. The micro-nano multimode star sensor system provided by the invention is small in size, high in reliability and low in manufacturing cost, and the satellite attitude can be corrected in real time. According to the data fusion method for the micro-nano multimode star sensor system provided by the invention, the angular velocity accuracy measured by the gyro is high, so that the star sensor can output high attitude data, and the satellite attitude correction precision is improved.

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