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Numerical Evaluation of On-Orbit Attitude Behavior for Microsatellites with Variable Shape Function

机译：变形状函数微卫星在轨姿态行为的数值评估

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摘要

An advanced attitude control technique for microsatellites which has missions required large angle manoeuver is investigated. In particular, the attitude control technique positively using anti-torque generated by driving appendages such as the solar array paddles is applied to a practical satellite system in this paper. Although the attitude variation occurs in this way had been investigated in areas such as a free-flying space robot, there is no attempt to make use of the variation practically for a main attitude control system of a satellite. In microsatellites this technique is to be effective because mass of microsatellites is small. Further microsatellites are able to perform challenging mission due to low-cost development. In this paper, we show that proposed technique is to be effective in a practical mission. First, the system dynamics and driving method of appendages is developed symbolically. Then, we constitute attitude control logic for VSAC. Finally, rest to rest attitude manoeuver is numerically simulated considering a concrete mission scenario. The simulation result reveals on-orbit behavior of the satellite system. From these result, we concluded that this attitude control method is to be effective in specific mission.
机译：研究了任务需要大角度机动的微卫星姿态控制技术。特别是，积极地利用驱动附件（例如太阳能电池板的桨叶）产生的抗扭矩的姿态控制技术被应用于实际的卫星系统中。尽管以这种方式发生的姿态变化已经在诸如自由飞行的太空机器人等领域进行了研究，但实际上并未尝试将这种变化用于卫星的主要姿态控制系统。在微卫星中，此技术是有效的，因为微卫星的质量很小。由于低成本的发展，更多的微卫星能够执行具有挑战性的任务。在本文中，我们表明所提出的技术在实际任务中是有效的。首先，象征性地开发了附件的系统动力学和驱动方法。然后，我们构成了VSAC的姿态控制逻辑。最后，在考虑具体任务场景的情况下，对休息姿势的机动进行了数值模拟。仿真结果揭示了卫星系统的在轨行为。从这些结果，我们得出结论，这种姿态控制方法将在特定任务中有效。

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