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首页> 外文期刊>Celestial Mechanics and Dynamical Astronomy: An international journal of space dynamics >Combined low-thrust propulsion and invariant manifold trajectories to capture NEOs in the Sun-Earth circular restricted three-body problem
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Combined low-thrust propulsion and invariant manifold trajectories to capture NEOs in the Sun-Earth circular restricted three-body problem

机译：结合低推力推进和不变歧管轨迹来捕获日地圆形受限三体问题中的近地天体

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摘要

In this paper, a method to capture near-Earth objects (NEOs) incorporating lowthrust propulsion into the invariant manifolds technique is investigated. Assuming that a tugboat-spacecraft is in a rendez-vous condition with the candidate asteroid, the aim is to take the joint spacecraft-asteroid system to a selected periodic orbit of the Sun-Earth restricted three-body system: the orbit can be either a libration point periodic orbit (LPO) or a distant prograde periodic orbit (DPO) around the Earth. In detail, low-thrust propulsion is used to bring the joint spacecraft-asteroid system from the initial condition to a point belonging to the stable manifold associated to the final periodic orbit: from here onward, thanks to the intrinsic dynamics of the physical model adopted, the flight is purely ballistic. Dedicated guided and capture sets are introduced to exploit the combined use of low-thrust propulsion with stable manifolds trajectories, aiming at defining feasible first guess solutions. Then, an optimal control problem is formulated to refine and improve them. This approach enables a new class of missions, whose solutions are not obtainable neither through the patched-conics method nor through the classic invariant manifolds technique.
机译：本文研究了一种将低推力推进结合到不变流形技术中的近地天体（NEO）的捕获方法。假设拖船航天器与候选小行星处于会合状态，目的是将联合航天器-小行星系统带到太阳-地球受限三体系统的选定周期性轨道上：地球周围的解放点周期轨道（LPO）或远距前进周期轨道（DPO）。详细地说，低推力推进是将航天器-小行星联合系统从初始状态带到属于与最终周期轨道相关的稳定流形的一点：从这里开始，这要归功于所采用的物理模型的内在动力学，这是纯粹的弹道飞行。引入了专用的导向和捕获装置，以利用低推力推进与稳定歧管轨迹的组合使用，旨在定义可行的首次猜测解决方案。然后，制定了一个最优控制问题以完善和改进它们。这种方法实现了新一类的任务，其解决方案既不能通过锥锥法也不能通过经典不变流形技术获得。

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