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对GPS实时定轨误差对卫星姿态确定的影响进行了分析。因用位置、速度确定的坐标转换矩阵无法直接给出姿态角确定误差的解析表达,基于近圆、近极轨轨道假设,根据位置、速度和开普勒轨道六要素间的转换关系,给出了小姿态角偏差条件下转换矩阵的全微分形式,进而给出了各姿态角关于各轴分量的偏导数形式,在分别分析位置和测速误差对姿态角影响的基础上,给出了综合的姿态角确定误差,推导了姿态确定误差的解析表达式。研究发现:速度矢量主要引起偏航角的误差,对俯仰和滚动方向几乎无影响;位置矢量主要引起俯仰和滚动轴的姿态角误差,对偏航角方向几乎无影响。仿真结果验证了分析的正确性,并发现GPS定轨误差引起的姿态角确定误差小于0.001°,基本可忽略。
The impact of GPS real-time orbit error on satellite attitude determination is analyzed. Due to the coordinate transformation matrix determined by the position and velocity, the analytical expression of the attitude determination error can not be directly given. Based on the assumption of near-circular or near polar orbital trajectory, the relationship between the position and velocity and the six elements of the Keplerian orbit is given The differential forms of the transformation matrices under the small angular misalignment conditions are given, and then the partial derivatives of each attitude angle with respect to the various axial components are given. Based on the analysis of the influence of position and velocity error on the attitude angles, Determination of attitude angle error, derivation of attitude determination error analytical expression. It is found that the velocity vector mainly causes the error of yaw angle and has almost no influence on the pitch and roll direction. The position vector mainly causes the attitude angle error of pitch and roll axis, and has almost no effect on the yaw angle direction. The simulation results verify the correctness of the analysis and find that the error of attitude determination caused by GPS orbit error is less than 0.001 ° and can be neglected basically.