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太阳帆航天器是一种新型航天器,被广泛设计应用于深空探测任务,它依靠太阳光压力产生推进力。通过改变太阳帆的姿态可以控制太阳帆航天器的轨道,因此姿态控制对太阳帆航天器的任务具有重要意义。为了获得足够大的推进力,太阳帆具有大尺度的柔性结构,因此太阳帆航天器具有大转动惯量和大柔性的动力学特性,这对其姿态控制带来了困难。而利用太阳帆的特殊结构可以设计出一些特殊的姿态控制机构,如中心控制杆和控制小帆等,降低控制成本,改善控制效果。该文在柔性太阳帆耦合动力学降阶模型的基础上,将太阳帆的控制机构简化为中心力矩控制和端点力控制,针对太阳帆单轴大角度机动过程,研究了两种控制方法下太阳帆柔性结构对其姿态控制的影响。研究表明,通过端点力控制可以有效减小太阳帆在姿态机动过程中姿态及结构的振动幅度,可以更好的完成太阳帆的姿态机动任务。
The solar sail spacecraft is a new type of spacecraft that has been widely designed for deep space exploration missions and relies on the pressure of the sun to generate propulsion. By changing the attitude of the solar sail to control the orbit of the solar sail spacecraft, attitude control is of great importance to the mission of the solar sail spacecraft. In order to obtain sufficient propulsive force, the solar sail has a large-scale flexible structure. Therefore, the solar sail spacecraft has a large inertia and a large flexible dynamic characteristic, which makes it difficult to control its posture. The use of special structure of the solar sail can design some special attitude control agencies, such as the center control rod and control small sails, reduce control costs and improve the control effect. Based on the reduction model of coupling dynamics of flexible solar sail, this paper simplifies the control mechanism of solar sail to center moment control and end point force control. According to the single-axis long-angle maneuvering process of solar sail, Effect of flexible structure of sail on attitude control. The research shows that the terminal force control can effectively reduce the amplitude of the attitude and structure of the solar sail during the attitude maneuvering, and can better accomplish the attitude maneuver task of the solar sail.