本文選題：撓性太陽帆板 + 姿態(tài)穩(wěn)定��； 參考：《哈爾濱工業(yè)大學》2015年碩士論文

【摘要】：縱觀現如今的航天技術飛速發(fā)展,不僅衛(wèi)星有效載荷對能源的需求越來越大,而且衛(wèi)星的姿態(tài)機動精度、穩(wěn)定度、機動時間等都提出了更高的要求。所以,如何提高太陽能帆板能量的轉化效率,如何處理好帶撓性太陽帆板衛(wèi)星姿態(tài)控制系統和撓性結構之間的耦合顯得至關重要。在這種背景下,本文從多角度出發(fā),對帶太陽帆板撓性衛(wèi)星的姿態(tài)穩(wěn)定和驅動機構驅動帆板對日定向的控制問題進行了細致的研究。本文首先研究了撓性衛(wèi)星動力學模型和帆板驅動機構模型,并且考慮了帆板驅動和系統不確定性引起的干擾,建立了帶撓性太陽帆板衛(wèi)星的變參數模型。針對帶太陽能帆板的撓性衛(wèi)星姿態(tài)穩(wěn)定的問題和太陽帆板對日定向過程中驅動機構平穩(wěn)驅動帆板的問題,提出了一種基于輸出反饋的PD控制方法,并證明了該控制律在李雅普諾夫意義下穩(wěn)定。以GOES-8號靜止軌道氣象衛(wèi)星為仿真研究對象,利用其公布的動力學參數,仿真表明:在PD控制作用下,帆板轉速存在明顯振蕩,不能滿足帆板平穩(wěn)驅動的要求。然后,針對這一問題,本文又提出了一種復合控制的方法。衛(wèi)星姿態(tài)穩(wěn)定采用的是滑模變結構控制,以其對外部擾動和參數攝動引起的不確定性具有魯棒性等優(yōu)點來應對帆板驅動和系統不確定性引起的干擾,并且還設計了步進電機自適應電流補償控制器用來抵消帆板驅動機構摩擦力矩和諧波力矩影響。同樣以GOES-8號衛(wèi)星為仿真研究對象,進行了三組仿真對比,分別是姿態(tài)滑模變結構+驅動機構自適應;姿態(tài)PD+驅動機構自適應;姿態(tài)滑模變結構+驅動機構PD,驗證了滑模變結構+驅動機構自適應控制系統的有效性,很明顯地提高了衛(wèi)星姿態(tài)控制的精度和穩(wěn)定度,而且改善了驅動機構驅動帆板對日定向的精度。
[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.
【學位授予單位】：哈爾濱工業(yè)大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V448.2

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本文編號：1910473