【摘要】：研究了剛性航天器的時(shí)延姿態(tài)穩(wěn)定控制問(wèn)題。首先建立了基于修正羅德里格斯參數(shù)(modified rodrigues parameters,MRPs)的航天器非線性狀態(tài)模型,具有確定上界的時(shí)延項(xiàng)在狀態(tài)反饋控制律中體現(xiàn)。通過(guò)構(gòu)造Lyapunov-Krasovskii泛函進(jìn)行穩(wěn)定性分析,由此得到保證系統(tǒng)漸近穩(wěn)定的線性矩陣不等式,依此設(shè)計(jì)狀態(tài)反饋控制系數(shù)矩陣�？紤]到航天器三軸間的耦合非線性項(xiàng),利用擴(kuò)張狀態(tài)觀測(cè)器(extended state observer,ESO)方法,設(shè)計(jì)了二階非線性擴(kuò)張狀態(tài)觀測(cè)器,以獲得航天器系統(tǒng)內(nèi)部狀態(tài)向量并用于狀態(tài)反饋控制律。為便于工程實(shí)際應(yīng)用,仿真中將MRPs響應(yīng)輸出轉(zhuǎn)換為歐拉角響應(yīng),仿真結(jié)果表明,本文所設(shè)計(jì)的控制系統(tǒng)能保證航天器三軸姿態(tài)穩(wěn)定。
[Abstract]:The problem of time delay attitude stability control for rigid spacecraft is studied. Firstly, a nonlinear state model of spacecraft based on modified Rodrigues parameter (modified rodrigues parameters,MRPs) is established. The time-delay term with the upper bound is represented in the state feedback control law. Based on the stability analysis of Lyapunov-Krasovskii functional, a linear matrix inequality (LMI) is obtained to guarantee the asymptotic stability of the system. The state feedback control coefficient matrix is designed accordingly. Considering the coupling nonlinear term between three axes of spacecraft, the second order nonlinear extended state observer is designed by using the extended state observer (extended state observer,ESO) method to obtain the internal state vector of the spacecraft system and use it in the state feedback control law. In order to facilitate practical engineering application, the MRPs response output is converted into Euler angle response by simulation. The simulation results show that the control system designed in this paper can ensure the stability of spacecraft three-axis attitude.
【作者單位】： 哈爾濱工業(yè)大學(xué)控制與仿真中心;
【分類號(hào)】：V448.2

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本文編號(hào)：2218502