文章提出了一种简单可行的方法,确定在卫星初始轨道上任意一点施加大小固定、方向任意的脉冲后生成轨道的可达区域;并对可达区域进行仿真验证了该方法的正确性和可行性.第2节和第3节内容主要以生成轨道为椭圆轨道的情况为例,分别研究初始轨道为圆轨道和椭圆轨道时卫星的可达区域,仿真结果与参考文献一致,从而证明了该方法的正确性和可行性.%Sections 1, 2 and 3 of the full paper present a method for determining the reachable domain of satellite trajectories generated by a single impulse with fixed magnitude and arbitrary direction applied at any point of the initial orbit of a satellite; in addition, they present the simulation results to verify preliminarily that our method is correct and feasible. The core of sections 2 and 3 is that we take the elliptic trajectory generated by coplanar single impulse and spatial single impulse as an example to analyze and simulate the reachable domain of a satellite traveling along the initial circular orbit and the initial elliptic orbit respectively. The simulation results, given in Figs. 1through 4, and their analysis show preliminarily that our method is in agreement with the method in Ref. 4, which treats the coplanar special case, and thus is plausibly correct and feasible.
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