基于线性化运动方程的超低轨飞行器轨道修正算法

Orbit Correction Strategy of LEO Vehicle Based on Linearized Orbital Motion Equation

超低轨飞行器受到大气的严重影响,需要不断地实施轨道修正才能在标称轨道附近飞行。文章针对超低轨飞行器的轨道保持问题,建立了考虑地球非球形J2项摄动和大气阻力摄动的线性化运动方程,给出了基于线性化方程的修正速度增量计算方法,并研究了补偿线性化误差的方法。数值仿真表明,该方法能够保证飞行器不超出要求的精度通道。对于轨道高度为120km的飞行器,飞行1h的最佳修正次数为6,所需速度增量为63.7971m/s。

It is very necessary to execute orbit correction for ultra-low-orbit vehicle , w hich is badly influenced by near-earth environment . The orbital motion equation which considered the non-spherical perturbation and atmospheric perturbation was linearized . Then , an impulse correction method was introduced and used to keep a near-earth vehicle flying along the standard orbit . Furthermore ,a method to eliminate errors caused by linearization was also studied . The feasibility of the correction method was validated by simulation . For a 120km-altitude vehicle , flying one hour , the optimal correction times is 6 , the required Dv is 63.797 1 m/s .