Artificial Periodic Orbits Around L1-Type Equilibrium Points for a Generalized Sail
Artificial Periodic Orbits Around L1-Type Equilibrium Points for a Generalized Sail
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DOI：
10.2514/1.g000904
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发表时间：
2015-06
影响因子：
2.6
通讯作者：
Generoso Aliasi;G. Mengali;A. Quarta
中科院分区：
文献类型：
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作者：
Generoso Aliasi;G. Mengali;A. Quarta
近年来，许多研究致力于利用具有连续推力推进系统的航天器的推进加速度来置换圆形限制性三体问题（CR 3BP）[1，2]的五个经典拉格朗日点的概念。为此，飞行器的推力必须足以平衡两个大质量物体的引力和行星际空间给定点的离心力。当这种情况发生时，可以生成新的人工平衡点（AEP）族，并且可以研究它们在位置和稳定性方面的主要属性。用于创建AEP的最常见的推进系统是光子太阳帆[3]，但存在使用电动推进器[4]或电动太阳风帆（E-sail）[5]生成AEP的示例。取代CR 3 BP中平衡位置的可能性是研究AEPs周围人工周期轨道（APO）存在的起点。例如，将共线L1型AEP用于科学使命要求将航天器置于具有适当离轴幅度的轨道，以将飞行器驱动到所谓的“太阳禁区”之外，从而避免太阳干扰下行链路遥测的问题[6]。如果采用适当的姿态控制策略来偏移推力方向，则使用偏离日[地+月]线5度的AEP是一种可能的选择[3]。尽管人们已经对共线经典拉格朗日点附近的周期轨道的特性进行了深入的研究[7]，但只有少数作者对APO的性质进行了研究。在大多数情况下，这些结果是使用基于太阳帆的太阳能电池板获得的，太阳能电池板研究助理，g. dia.unipi.it †教授，g. mengali@ing.unipi.it，AIAA高级成员。副教授，a.quarta@ ing.unipi.it。AIAA副研究员。
Introduction In recent years, many studies have been dedicated to the concept of displacing the five classical Lagrangian points of the Circular Restricted Three-Body Problem (CR3BP) [1, 2], using the propulsive acceleration of a spacecraft with a continuous-thrust propulsion system. To that end, the vehicle’s thrust must be sufficient for balancing both the gravitational pull of the two massive bodies and the centrifugal force at a given point of the interplanetary space. When this happens, new families of Artificial Equilibrium Points (AEPs) may be generated and their main properties, in terms of location and stability, may be investigated. The most commonly proposed propulsion system for creating AEPs is the photonic solar sail [3], but examples exist in which the AEPs are generated using an electric thruster [4] or an electric solar wind sail (E-sail) [5]. The possibility of displacing an equilibrium position in the CR3BP is the starting point to investigate the existence of Artificial Periodic Orbits (APOs) around AEPs. For example, the use of collinear L1-type AEPs for a scientific mission requires the spacecraft to be placed into an orbit with a suitable out-of-axis amplitude to drive the vehicle outside the so called “solar exclusion zone”, thus avoiding problems of solar interference with down-link telemetry [6]. The use of an AEP with 5 deg offset from the Sun-[Earth+Moon] line is a possible choice [3], provided that a suitable attitude control strategy is employed to offset the thrust direction. Even though the characteristics of periodic orbits have been thoroughly studied around the collinear classical Lagrangian points [7], the properties of APOs have been investigated by a few authors only. In most cases the results have been obtained using a solar sail based ∗Research Assistant, g.aliasi@dia.unipi.it †Professor, g.mengali@ing.unipi.it. Senior Member AIAA. ‡Associate Professor, a.quarta@ing.unipi.it. Associate Fellow AIAA.