A maneuver called “Aerogravity Assisted” is known in the literature to increase the energy gains given by a close approach between a spacecraft and a planet using the atmosphere of the planet. Several previous papers showed the importance of this topic in different aspects. The present paper has the goal of studying the effects of the spacecraft rotation in this maneuver. This rotation implies in a variable ballistic coefficient and this fact can change the results of the maneuver. Several masses, sizes and angular velocities will be tested and the effects of these parameters will be measured. The dynamical model considers the atmosphere of the Earth, in terms of drag, the gravitational fields of the Earth and the Sun, assumed to be points of mass, and the rotating spacecraft. The Earth and the Sun are assumed to be in circular coplanar orbits around their common center of mass. The equations of motion are the ones given by the circular planar restricted three-body problem with the addition of the forces generated by the atmospheric drag. The primary objective is to map the energy variations of the spacecraft orbits due to this close approach as a function of the spacecraft angular velocity. This rotation can be used as control of the maneuver to try to reach different goals.

中文翻译：

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航天器在大气与地球接近时的自转影响

在文献中已知一种称为“空气重力辅助”的动作，其通过使用行星大气来增加航天器与行星之间的紧密接近所提供的能量增益。先前的几篇论文都在不同方面表明了该主题的重要性。本文的目的是研究这种机动中航天器旋转的影响。该旋转暗示可变的弹道系数，并且该事实可以改变操纵的结果。将测试几种质量，大小和角速度，并测量这些参数的影响。动力学模型从阻力，地球和太阳的重力场（假定为质量点）以及旋转的航天器的角度考虑了地球大气。假定地球和太阳围绕它们共同的重心处于圆形共面轨道。运动方程是由圆形平面约束三体问题加上大气阻力产生的力所给出的方程。主要目标是根据这种接近的方法，根据航天器角速度绘制航天器轨道的能量变化图。该旋转可以用作操纵的控制，以尝试达到不同的目标。