Planar orbits about a triaxial body: application to asteroidal satellites
Planar orbits about a triaxial body: application to asteroidal satellites
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DOI：
10.1006/icar.1993.1134
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发表时间：
1993-10
期刊：
影响因子：
3.2
通讯作者：
B. Chauvineau;P. Farinella;F. Mignard
中科院分区：
文献类型：
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作者：
B. Chauvineau;P. Farinella;F. Mignard
我们研究了一颗强三轴主卫星绕惯性主轴旋转的小卫星的动力学行为，但仅限于平面情况（卫星轨道位于主卫星的“赤道”对称平面上）。由于我们主要感兴趣的是将结果应用于（天然和人造）小行星卫星的动力学，因此我们详细研究了轴向比为2:1:1/ 2、旋转周期为5至40小时的三轴椭球原星的情况。我们采用经典的庞加莱截面法来展示数值积分实验的结果，特别展示了在旋转参照系中，原星的三轴形状如何“扰动”了开普勒问题的动力学，在旋转参照系中原星是固定的。我们发现在主卫星自转周期和卫星轨道周期之间的1/1共振附近出现了一个相当大的混沌区。另一个较小的混沌区包括逆行轨道靠近主星系，对应的初始速度接近逃逸速度。混沌带随着原星系旋转周期的缩短而变得越来越大。然而，靠近原星的规则轨道也确实存在，其中一些轨道被共振效应锁定。最后，我们已经确定了最适合小行星（或彗星）人造卫星的轨道，但要满足以下要求：接近（尽管非碰撞），避免强烈的混沌行为，以及受（先验未知的）小行星质量分布的微弱影响。
Abstract We have studied the dynamical behavior of a small satellite of a strongly triaxial primary rotating about a principal axis of inertia, restricting ourselves to the planar case (satellite orbits lying in the "equatorial" symmetry plane of the primary). Since we were mainly interested in applying the results to the dynamics of(natural and artificial) asteroidal satellites, we have studied in detail the case of a triaxial ellipsoidal primary, with axial ratios 2:1: 1/ 2 and rotation periods ranging from 5 to 40 hr. We have employed the classical method of Poincare's surfaces of section to display the results of numerical integration experiments, showing in particular how the triaxial shape of the primary "perturbs" the dynamics of the Kepler problem seen in the rotating reference frame where the primary is fixed. We have found that a sizeable chaotic zone appears near the 1/1 resonance between the rotation period of the primary and the orbital period of the satellite. Another smaller chaotic zone includes the retrograde orbits passing close to the primary and corresponding to initial velocities close to the escape velocity. The chaotic zones become larger and larger for shorter rotation periods of the primary. However, regular orbits staying close to the primary do also exist, some of them being locked by resonant effects. Finally, we have identified the most suitable orbits for an artificial satellite of an asteroid (or a comet), subject to the requirements of being close (though non-collisional), of avoiding strongly chaotic behavior, and of being weakly affected by the (a priori unknown) asteroidal mass distribution.