Study on Experimental Design and Verification of Attitude/Orbital Control System for a Solar Sail

首先，研究了太阳帆旋转航天器在地球和行星际轨道上的姿态和轨道动力学，为日本宇宙航空研究开发机构（ISAS/JAXA）空间科学研究所未来的深空探测进行研究。数值模拟估计了其旋转速率和质心与压力中心之间不确定的偏移量对姿态变化的影响。然后，考虑到计算的影响量，本研究设计并组装了一个旋转太阳帆姿态控制系统验证的地面实验系统。实验系统利用地球重力模拟太阳辐射压力（SRP）；原计划采用气流作为SRP的建模，但发现气流扰动和涡流容易对系统产生扰动力和扭矩。此外，还利用反平衡系统进行了重力补偿，实验模拟了由于船帆加速度反作用力对其有效载荷质量产生的小惯性力。此外，系统可以通过移动放置在两轴平衡控制臂顶端的有效载荷质量来控制其cm/cp偏移。实验系统验证了其作为旋转太阳帆系统地面验证装置的基本性能，测量了每个轴上的诱导扭矩和力，以改变cm/cp偏移量和旋转速率。

First, this research examined the attitude and orbital dynamics of spinning solar sail spacecraft on earth-and interplanetary-orbit, which is investigated for future deep space exploration in Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (ISAS/JAXA). Numerical simulations estimated the influence of its spinning rate and an uncertain offset between its center-of-mass (cm) and center-of pressure (cp) on the attitude variation.Then, considering an amount of the calculated influence, this research designed and assembled a ground experimental system for validation of an attitude control system for a spinning solar sail. The experimental system simulates a solar radiation pressure (SRP) force using earth gravity force; originally, air flow were supposed to be employed as modeling for SRP, but it was turned out that flow disturbance and vortex easily generates disturbance force and torque for the system. Besides, small inertia force acting its payload mass due to counter effect of sail acceleration is also experimentally simulated through gravity force compensation using a counter balance system. Furthermore, the system can control its cm/cp offset by moving the payload mass placed at the tip of a two-axis gimbaled control boom.The experimental system verified its fundamental performance as a ground-placed validation setup for a spinning solar sail system, in measuring induced torque and force in each axis for changing the cm/cp offset and spinning rate.