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Attitude dynamics and stability of a flexible gravity-gradient stabilized spacecraft in orbit raising maneuvers.

机译：柔性重力梯度稳定航天器在升轨道中的姿态动力学和稳定性。

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This thesis examines the dynamic response of a flexible Gravity-Gradient Stabilized Spacecraft (GOSS) comprising coupled orbital, attitude, and vibrational motions. Highly nonlinear, coupled equations of motion are developed. The fourth order Runge-Kutta numerical scheme is applied to solve these equations. The response of the spacecraft is analyzed in simulations of a multi-stage maneuver from Low Earth Orbit (LEO) to Geosynchronous Earth Orbit (GEO) altitude using the Hohmann transfer method. Three maneuver conditions are considered here. First, the spacecraft attitudes are considered not to be affected by the thruster firing. Second, the thruster firing effects are taken into account. Third, the effects of imperfect thruster firing, which creates parasitic torques, is considered. The results indicate the stability of the response depends on the eccentricity of the transfer orbit. The thruster's impulse effect helps drive the system unstable. The presence of parasitic torques about the roll and yaw axes leads to attitude instability. Parasitic torque about the pitch axis can be tolerated as long as its magnitude is below some value. Flexibility of the linkage does not affect the orbital or attitudinal responses to the maneuver, except when the thruster's impulse is included in the analysis. Inclusion of the thrusting process in the simulation has the potential for exciting high frequency characteristics of the model.
机译：本文研究了包括轨道，姿态和振动运动在内的柔性重力梯度稳定航天器（GOSS）的动力响应。建立了高度非线性的耦合运动方程。应用四阶Runge-Kutta数值格式求解这些方程。使用霍曼转移方法，在从低地球轨道（LEO）到地球同步地球轨道（GEO）高度的多阶段机动仿真中，分析了航天器的响应。这里考虑三个操纵条件。首先，认为航天器的姿态不受推进器发射的影响。其次，要考虑推进器的点火效果。第三，考虑了产生寄生扭矩的不完美的推进器点火的影响。结果表明，响应的稳定性取决于转移轨道的偏心率。推进器的脉冲效应有助于使系统不稳定。围绕侧倾和偏航轴的寄生转矩的存在会导致姿态不稳定。只要螺距轴的大小在某个值以下，就可以容许围绕螺距轴的寄生扭矩。联动的灵活性不影响机动的轨道或姿态响应，除非在分析中包括推进器的脉冲。将推力过程包括在仿真中可能会激发模型的高频特性。

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