基于等倾角姿态控制的自旋稳定卫星姿态预测方法

本发明涉及一种等倾角姿态控制的自旋稳定卫星姿态预测方法，所述方法以自旋稳定卫星在参考坐标系下的初始姿态、目标姿态和姿控量为输入，对卫星姿态进行预测，计算麦卡托图坐标，并对太阳角、北红外弦宽、南红外弦宽进行预测，根据已经计算出的姿态控制参数(姿控量)和给定的控制方式计算出卫星姿态因受控而发生姿态变化的趋势，同时计算出因姿态变化而导致红外弦宽角、太阳角的变化趋势。本发明方法适应于自旋稳定卫星以等倾角进动方式进行姿态控制的姿态预测。 The invention relates to a self-rotation stabilized satellite attitude prediction method based on equal-inclination-angle attitude control. According to the method, by taking an initial attitude, a target attitude and an attitude control amount of a self-rotation stabilized satellite in a reference coordinate system as input, a satellite attitude is predicted, an Mercato graph coordinate is calculated, a sun angle, the north infrared outer chord width and the south infrared outer chord width are predicted, according to a calculated attitude control parameter (the attitude control amount) and agiven control mode, the attitude changing trend of the satellite attitude caused by the control is calculated, and meanwhile, the changing trends of the infrared outer chord wide angel and the sun angle due t