Spacecraft attitude determination method and system

The invention provides a spacecraft attitude determination method and system, and the method comprises the steps: providing an orbit compass attitude determination method which is used for determiningthe attitude of a spacecraft through employing a gain coefficient; generating an optimal selection strategy of a gain coefficient in the orbit compass attitude determination method based on a Chebyshev filter; generating an optimal gain coefficient according to the optimal selection strategy, and generating a state transition matrix by using the optimal gain coefficient; generating an orbit compass attitude determination method in a discretization form based on the state transition matrix; and determining the attitude of the spacecraft by using the orbit compass attitude determination methodin the discretization form. 本发明提供了一种航天器姿态确定方法及系统，包括：提供轨道罗盘定姿方法，所述轨道罗盘定姿方法用于利用增益系数确定航天器的姿态；基于切比雪夫滤波器，生成所述轨道罗盘定姿方法中的增益系数的最优选取策略；根据所述最优选取策略，生成最优增益系数，并且利用所述最优增益系数，生成状态转移矩阵；基于所述状态转移矩阵，生成离散化形式的轨道罗盘定姿方法；以及利用所述离散化形式的轨道罗盘定姿方法进行航天器姿态确定。