IGSO satellite Kepler orbital element correction method based on perigee angular distance correction

The invention provides an IGSO satellite Kepler orbital element correction method based on perigee angular distance correction, and belongs to the field of satellite navigation system constellation simulation. According to the method, six ephemeris of Kepler orbits of a satellite are used as simulation parameters, the fixed-point longitude when the IGSO satellite flies over the equator is used as a fixed value, the angle difference between the right ascension of the initial ascending node of the orbits and the fixed value is calculated, time difference information is obtained in combination with the rotation angular speed of the earth, perigee angular distance of the ephemeris parameters is corrected, and the attitude of the earth is corrected. The sub-satellite point trajectory obtained through simulation is consistent with the theoretical trajectory, and the method can be used in the field of satellite navigation system constellation simulation. 本发明提出了一种基于近地点角距校正的IGSO卫星开普勒轨道根数修正方法，属于卫星导航系统星座仿真领域。本发明以卫星的开普勒轨