关键词: font-family:宋体, 姿态确定')">">姿态确定, 方向余弦矩阵, 四元数, 非互易误差, 对偶四元数')">">

Abstract:

The quaternion calculation for spacecraft attitude determination is investigated in this paper，including the transformation between quaternion and the direction cosine matrix，the quaternion differential equation，the selection of time steps for integrating the quaternion equation，and the compensation methods for the noncommutativity error in high dynamic motion．The dual quaternion is also addressed．

Key words: font-family:Calibri, sans-serif, attitude determination">attitude determinationfont-family:宋体, ')">">, font-family:Calibri, sans-serif, direction cosine matrix">direction cosine matrixfont-family:宋体, ')">">, font-family:Calibri, sans-serif, quatemion"> quatemionfont-family:宋体, ')">">, font-family:Calibri, sans-serif, noncommutatiVity error"> noncommutatiVity errorfont-family:宋体, ')">">, font-family:Calibri, sans-serif, dual quatemion">dual quatemion')">">