The invention provides a satellite attitude guide angle calculation method and system based on GNSS absolute positioning data, and the method comprises the steps: S1, converting the time, position and speed in the GNSS real-time absolute positioning data into an inertial coordinate system, and obtaining the position and speed in the inertial coordinate system; s2, recursion is carried out on the position and speed numerical integration at the GNSS real-time absolute positioning time to the current satellite time, and the position and the speed at the current satellite time moment are obtained; s3, converting the position and speed information at the current moment to obtain orbit parameters at the corresponding moment; and S4, calculating a yaw guide angle and a pitching guide angle at the current moment according to the orbit parameters at the current satellite time moment. According to the method, the satellite attitude guide angle can be calculated in real time with high precision, high-precision attitude control is effectively supported, image deformation caused by earth rotation is effectively compensated, and the imaging quality is improved.
本发明提供了一种基于GNSS绝对定位数据的卫星姿态导引角计算方法及系统,包括:步骤S1:根据GNSS实时绝对定位数据中的时间、位置、速度转换到惯性坐标系下,得到惯性坐标系下的位置、速度;步骤S2:将GNSS实时绝对定位的时间下位置速度数值积分递推至当前星时,得到当前星时时刻的位置和速度;步骤S3:将当前时刻的位置速度信息转换得到对应时刻的轨道参数;步骤S4:根据当前星时时刻轨道参数,计算当前时刻偏航导引角和俯仰导引角。本方法可以实时高精度计算卫星姿态导引角,有效支持高精度的姿态控制,有效补偿地球自转引起的图像形变,提高成像质量。
Satellite attitude guide angle calculation method and system based on GNSS absolute positioning data
基于GNSS绝对定位数据的卫星姿态导引角计算方法及系统
2023-04-04
Patent
Electronic Resource
Chinese
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