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利用太阳引力摄动与月球绕飞设计的地月转移轨道 (飞月轨道 ) ,与霍曼转移相比 ,虽然飞行时间较长 (约三、四个月 ) ,但可显著节省速度增量 (可达 15 0米 /秒 ) ,对无人月球探测器尤为适合。应用平面圆型限制性四体问题动力学模型 ,选择从月球出发的初始条件。借助“地心距 时间曲线” ,从平面圆型限制性四体问题转换为一般的限制性四体问题。通过典型模拟计算 ,分析负向积分 (从月球轨道出发 )初始轨道参数及太阳方位对月球探测器轨迹的影响 ,探讨飞月轨道引力捕获的工程设计方法
The use of solar gravitation perturbation and lunar lunar orbit transfer lunar orbit (lunar orbit), compared with the Hohmann transfer, although the flight time is longer (about three or four months), but can significantly save the speed increase ( Up to 15 0 m / s), especially for unmanned lunar rover. Using the planar circular constrained four-body problem kinetic model, the initial conditions starting from the moon are chosen. With the help of “geocentric time curve”, the problem of the planar four-body constrained problem is transformed into a general restricted four-body problem. Through the typical simulation calculation, the influence of the initial integral of the negative integral (from lunar orbit) to the lunar probe’s trajectory is analyzed, and the engineering design method of the lunar orbit gravity capture