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首页> 外文会议>AAS/AIAA Space Flight Mechanics Meeting; 20070128-0201; Sedona,AZ(US) >ORBITAL MANEUVERS USING A CLOSE APPROACH IN A RETURN PASSAGE BY THE MAIN BODY
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ORBITAL MANEUVERS USING A CLOSE APPROACH IN A RETURN PASSAGE BY THE MAIN BODY

机译：主身体在回程中采用封闭方法进行的轨道操纵

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摘要

The objective of this paper is to study optimal space maneuvers that search for the minimum fuel consumption for interplanetary missions that consist of a spacecraft leaving one celestial body and going back to this same body, using this return passage to perform a Swing-By with the mother planet to change its velocity, energy and angular momentum. This is called here "Swing-By Maneuvers using Consecutive Collision Orbits". During this approach, the space vehicle place itself in another orbit of the interest of the mission. The dynamics used to solve this problem is the traditional model of the Restricted Three Body Problem, so it is assumed that the three bodies involved are mass points and do not suffer external disturbances. The change after the Swing-by in terms of the velocity variation (△V) and the energy variation (△E) are obtained. Several orbits of multiple encounters and Swing-By are simulated.
机译：本文的目的是研究最佳空间机动，以寻找行星际飞行任务的最小燃料消耗，这种飞行任务是由一个航天器离开一个天体并返回到同一天体，然后利用该返回通道与太空飞船一起执行“摇摆”运动。母行星改变其速度，能量和角动量。这在此处称为“使用连续碰撞轨道的摆动操纵”。在这种方法中，航天器将自己置于任务感兴趣的另一个轨道上。用于解决该问题的动力学是受限三体问题的传统模型，因此假设所涉及的三个体是质量点，并且不受外部干扰。获得了摆动后速度变化（△V）和能量变化（△E）的变化。模拟了多次相遇和Swing-By的几个轨道。

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