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Analysis of Orbit-Attitude Coupling of Spacecraft Near Small Bodies

机译：小型物体附近航天器的轨道-姿态耦合分析

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The design and analysis of proximity operations around small solar system bodies is a challenging and complex task. This is mainly due to several destabilizing perturbations such as nonuniform rotating gravity field of the small body, solar radiation pressure, and solar tide. Another important perturbation which is often neglected during the design of close proximity operations is the coupling between orbital and attitude motion of the spacecraft. In most small body missions, the spacecraft is considered to be a point mass as compared to the asteroid, and this assumption has implications on the mission design. This paper compares the dynamics of a rigid body and a point mass in proximity to a small solar system body modeled as a triaxial ellipsoid with uniform density. The small body's gravity field is described using the second degree and order spherical harmonic expansion. The sun's gravity is also considered to act on the asteroid, as well as the point mass and rigid body. A Lie group variational integrator is used to numerically simulate the full (translational and rotational) dynamics of the rigid body. Numerical simulations show the trajectory of the rigid body rapidly diverges from that of the point mass due to the orbit-attitude coupling for small bodies modeled after Near Earth Object 25143 Itokawa. Possible implications on the performance of model-based spacecraft control and on the station-keeping budget if the orbit-attitude coupling is not accounted for in the dynamics model, are presented.
机译：围绕小型太阳系天体的近距离运行的设计和分析是一项艰巨而复杂的任务。这主要是由于一些不稳定的扰动，例如小物体的旋转重力场不均匀，太阳辐射压力和太阳潮。在近距离操作的设计中经常忽略的另一个重要扰动是航天器的轨道运动与姿态运动之间的耦合。在大多数小型身体飞行任务中，与小行星相比，航天器被认为是点质量，这一假设对飞行任务的设计有影响。本文比较了一个刚性的物体和一个小太阳系物体附近的点质量的动力学，该物体被建模为具有均匀密度的三轴椭圆体。小物体的重力场是使用二阶和阶数球谐展开来描述的。太阳的重力也被认为作用于小行星，点质量和刚体。李群变分积分器用于数值模拟刚体的全部（平移和旋转）动力学。数值模拟表明，由于以近地物体25143 Itokawa为模型的小物体的轨道-高度耦合，刚体的轨迹与点质量的轨迹迅速不同。如果没有在动力学模型中考虑轨道-高度耦合，则可能对基于模型的航天器控制的性能以及对站位保持预算的影响。

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