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目的考虑在Hill限制性三体问题的条件下,研究太阳帆从地球附近的圆轨道到人工拉格朗日点的轨道转移问题。方法利用能量分析的方法,在地球附近的停泊轨道施加脉冲同时展开太阳帆,让太阳帆进入人工拉格朗日点的转移轨道,在无主动控制的情况下,太阳帆以某一姿态角沿转移轨道被动稳定地飞行到人工拉格朗日点。结果利用解析方法分析了轨道转移的理论最优值,并与数值结果进行比较发现两者非常接近。结论当太阳帆的姿态角保持不变的情况下,太阳帆的姿态角决定了太阳帆的广义能量常数。姿态角在几个区域内时,存在着最优转移轨道。在这些区域内,可以选择合适的姿态角使得从某一个轨道高度到人工拉格朗日点的转移能量最小,同时转移时间也较小。
Aim To consider the problem of orbital transfer of solar sails from a circular orbit near Earth to an artificial Lagrange point under the condition of Hill restricted trisomy. Methods By means of energy analysis, pulses are applied to the mooring orbit around the earth and the solar sail is launched to allow the solar sail to enter the artificial orbit of the artificial Lagrange point. Under the condition of no active control, Transfer orbit passively and steadily fly to artificial Lagrange point. Results The optimal theoretical value of orbital transfer was analyzed by analytical method and compared with the numerical results, the two values were very close. Conclusions The attitude of the solar sail determines the generalized energy constant of the solar sail when the attitude of the solar sail remains the same. When the attitude angle is in a few areas, there exists an optimal transfer orbit. In these regions, the appropriate attitude angle can be selected to minimize the transfer energy from one orbital height to the artificial Lagrangian point, with less transfer time.