卫星在轨道平面内的可达范围研究

REACHABLE DOMAIN OF A SATELLITE WITH A COPLANAR IMPULSE APPLIED

对在初始轨道上施加平面内幅值固定的脉冲后卫星的可达范围进行了研究.考虑脉冲幅值较小、生成轨道均为椭圆的情况.根据平面曲线族包络线的定义,针对不同任务的需求,考虑脉冲施加点固定而方向任意、脉冲施加点任意而方向固定、脉冲施加点和方向均任意的3种情况,分别给出了确定可达范围边界的方法.数值仿真表明:所提出的方法能够确切描述卫星可达范围的边界,所得结论对初始椭圆轨道的偏心率没有限制,可以用于单颗卫星机动范围的评估和不同卫星间安全距离的设计.

This paper studies the reachable domain of a satellite after a coplanar single impulse with fixed magnitude applied.On the assumption that all of the generated trajectories are ellipses due to the small amplitude impulse,the reachable domain is bounded.According to the definition of the envelope of the curve family in a plane,the boundary of reachable domain is revealed respectively for three situations,namely,the point to apply impulse is fixed and the direction is arbitrary,the point to apply impulse is arbitrary and the direction is fixed,both the point to apply impulse and the direction are arbitrary.The simulation results verify the validity of the present approach.The conclusion has no restriction on the eccentricity of the initial elliptic orbit,and fits for the situation of initial elliptic orbit with large eccentricity.