基于变参数模型的太阳帆板卫星姿态控制研究

发布时间：2018-05-19 14:32

本文选题：挠性太阳帆板 + 姿态稳定　；参考：《哈尔滨工业大学》2015年硕士论文

【摘要】：纵观现如今的航天技术飞速发展,不仅卫星有效载荷对能源的需求越来越大,而且卫星的姿态机动精度、稳定度、机动时间等都提出了更高的要求。所以,如何提高太阳能帆板能量的转化效率,如何处理好带挠性太阳帆板卫星姿态控制系统和挠性结构之间的耦合显得至关重要。在这种背景下,本文从多角度出发,对带太阳帆板挠性卫星的姿态稳定和驱动机构驱动帆板对日定向的控制问题进行了细致的研究。本文首先研究了挠性卫星动力学模型和帆板驱动机构模型,并且考虑了帆板驱动和系统不确定性引起的干扰,建立了带挠性太阳帆板卫星的变参数模型。针对带太阳能帆板的挠性卫星姿态稳定的问题和太阳帆板对日定向过程中驱动机构平稳驱动帆板的问题,提出了一种基于输出反馈的PD控制方法,并证明了该控制律在李雅普诺夫意义下稳定。以GOES-8号静止轨道气象卫星为仿真研究对象,利用其公布的动力学参数,仿真表明:在PD控制作用下,帆板转速存在明显振荡,不能满足帆板平稳驱动的要求。然后,针对这一问题,本文又提出了一种复合控制的方法。卫星姿态稳定采用的是滑模变结构控制,以其对外部扰动和参数摄动引起的不确定性具有鲁棒性等优点来应对帆板驱动和系统不确定性引起的干扰,并且还设计了步进电机自适应电流补偿控制器用来抵消帆板驱动机构摩擦力矩和谐波力矩影响。同样以GOES-8号卫星为仿真研究对象,进行了三组仿真对比,分别是姿态滑模变结构+驱动机构自适应;姿态PD+驱动机构自适应;姿态滑模变结构+驱动机构PD,验证了滑模变结构+驱动机构自适应控制系统的有效性,很明显地提高了卫星姿态控制的精度和稳定度,而且改善了驱动机构驱动帆板对日定向的精度。
[Abstract]:With the rapid development of space technology nowadays, not only the demand of satellite payload for energy is increasing, but also the attitude maneuvering accuracy, stability, and maneuvering time of satellite are required to be higher and higher. Therefore, how to improve the energy conversion efficiency of solar panels and how to deal with the coupling between satellite attitude control system with flexible solar panels and flexible structures is very important. In this context, the attitude stability of flexible satellite with solar panels and the control of the diurnal orientation of the driving mechanism are studied in detail in this paper. In this paper, the dynamic model of flexible satellite and the driving mechanism model are studied, and considering the disturbance caused by the system uncertainty, a variable parameter model with flexible solar panel satellite is established. A PD control method based on output feedback is proposed to solve the problem of attitude stability of flexible satellite with solar panels and the problem of stationary driving of the driving mechanism in the course of solar panel orientation. It is proved that the control law is stable in the sense of Lyapunov. Taking GOES-8 geostationary orbit meteorological satellite as the simulation object and using its published dynamic parameters, the simulation results show that, under the control of PD, there is obvious oscillation in the speed of the canvas, which can not meet the requirements of the smooth driving of the sailing board. Then, in order to solve this problem, a compound control method is proposed in this paper. Sliding mode variable structure control is used in attitude stabilization of satellite. It is robust to the uncertainties caused by external disturbances and parameter perturbations to deal with the disturbances caused by panel driving and system uncertainties. The adaptive current compensation controller of stepping motor is also designed to counteract the influence of friction moment and harmonic moment of the plate-driven mechanism. At the same time, taking GOES-8 satellite as the simulation research object, three groups of simulation comparisons are carried out, which are adaptive attitude sliding mode variable structure driving mechanism, attitude PD driving mechanism adaptive, and so on. The adaptive control system of sliding mode variable structure driving mechanism is proved to be effective, and the precision and stability of satellite attitude control are obviously improved. Moreover, the precision of driving sail board to day orientation is improved.
【学位授予单位】：哈尔滨工业大学
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V448.2

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