实现轨道偏心率协调控制的卫星轨道维持方法

Low-Earth-Orbit Maintenance for ImprovingRemote Sensing in China

针对太阳同步轨道卫星的轨道捕获和保持中，发动机所提供的周向力会同时改变轨道半长轴a和偏心率矢量e这一问题，根据卫星拉格朗日运动方程，提出一种轨控策略，半长轴和偏心率控制在双脉冲控制时可以同时实现，且一般可以选择一个变轨点在地面测控站范围内。计算结果验证了该轨控方案的有效性。

Remote sensing requires that orbit parameters of satellites, whose orbit altitude is less than 1000 km, must be maintained strictly at specified values. These orbit parameter requirements for specific problem here are: orbit inclination should not deviate more than 0.01° in 98.8°; semi-major should deviate less than 1 km in 850 km; eccentricity should be less than 3.4×10-3. The difficulty in satisfying the three requirements lies in that semi-major and eccentricity are coupled, i.e., satisfaction of semi-major requirement leaves eccentricity requirement unsatisfied, and vice versa. The research proposed a simple model which decouples semi-major and eccentricity, i.e., satisfaction can be done at one time without worrying about endless iterations.