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首页> 外文期刊>Journal of Guidance, Control, and Dynamics >Optimal Satellite Transfers Using Relative Motion Dynamics
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Optimal Satellite Transfers Using Relative Motion Dynamics

机译：使用相对运动动力学的最佳卫星传输

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Afirst-order approximation of optimal two-burn transfers between satellite orbitswithin a formation is presentednand discussed. The orbital transfer problem is based on the well-known fact that, to first order, such orbits arenelliptic, with centers at the target or offset in the in-track direction. The methodology allows for a target in an(generally) elliptic orbit in its motion about the center of force. The solution obtained makes use of a transformationnof the problem to the reference frame of an auxiliary target in circular orbit in the inertial frame. The total requirednju0001vj is expressed in terms of the identifying parameters for the initial and final orbits in the formation, correspondingnto their respective sizes as measured by their minor axes, location of their centers, and their orientation. Thisnexpression allows for numerical parametric studies in the case where the initial and final orbits are in the same ornparallel planes. It is shown that the optimal total ju0001vj depends on the relative sizes of the orbits and the distancenbetween their centers. When the initial and final orbits are concentric, four optimal two-burn transfers, all of thensame total ju0001vj, are identified. It is further shown that the optimal ju0001vj changeswith the distance between the centersnof the orbits and attains aminimumwhen this distance is about 2.2 times the difference between theminor axes of thenorbits.
机译：提出并讨论了编队内卫星轨道之间最佳两次燃烧的一阶近似。轨道转移问题是基于这样一个众所周知的事实：首先，这种轨道呈椭圆形，中心在目标上，或者在轨道内方向偏移。该方法允许目标绕力中心在（通常）椭圆轨道上运动。所获得的解决方案利用了将问题转换为惯性系中圆形轨道上辅助目标的参考系的方法。总所需的nju0001vj用地层中初始轨道和最终轨道的识别参​​数表示，对应于其各自的大小（通过其短轴，中心位置和方向测量）。当初始轨道和最终轨道在相同或平行的平面中时，这种表达式允许进行数值参数研究。结果表明，最佳总ju0001vj取决于轨道的相对大小及其中心之间的距离。当初始轨道和最终轨道是同心的时，将识别出四个最优的两次燃烧转移，然后全部相同，即全部ju0001vj。进一步表明，最佳ju0001vj随轨道中心n之间的距离而变化，并且当该距离约为轨道副轴之间的差的2.2倍时达到最小值。

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