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为设计空间合作目标任务中各卫星间的安全距离,研究在初始椭圆轨道上施加一次脉冲后卫星的可达范围。考虑脉冲幅值较小,因此卫星的可达范围有界。针对脉冲位于轨道面内的情况,令脉冲的幅值固定而施加位置和方向均任意,推导了生成轨道的运行规律,提出了确定卫星可达范围的优化法,该方法能够直接给出边界点的真近点角。通过与拟合法的结果进行对比表明,对于初始轨道偏心率不同的情况,采用优化法均能够实现确定卫星可达范围的目的。
In order to design the safety distance between the satellites in the mission of space cooperation, the reachable range of the satellite after applying a pulse on the initial elliptical orbit is studied. Considering the pulse amplitude is small, so the satellite reachable range bounded. Aiming at the situation that the pulse is located in the orbital plane, the amplitude of the pulse is fixed and the position and direction are applied arbitrarily, the operation law of the generated orbit is deduced, and the optimization method for determining the reachable range of the satellite is proposed. The method can directly give the boundary point Really close point. The comparison with the result of fitting shows that the optimal method can be used to determine the reachable range of satellites for different initial eccentricity of orbits.