本文關(guān)鍵詞： 航天器編隊(duì) 非線性系統(tǒng) 多李雅普諾夫法 脈沖切換 駐留時(shí)間法 穩(wěn)定性 不穩(wěn)定模態(tài) 容錯(cuò)控制　出處：《南京航空航天大學(xué)》2015年碩士論文　論文類(lèi)型：學(xué)位論文

【摘要】：本文主要研究一類(lèi)變組成航天器編隊(duì)的容錯(cuò)控制設(shè)計(jì)問(wèn)題,航天器編隊(duì)飛行是如今航天領(lǐng)域的一個(gè)研究熱點(diǎn),不管是從軍事戰(zhàn)略還是出于民用目的,面對(duì)越來(lái)越復(fù)雜的空間任務(wù),單一的隊(duì)形已無(wú)法滿足需求。為了完成特定的空間任務(wù),編隊(duì)中的某些航天器可能會(huì)發(fā)生對(duì)接、分離、離開(kāi)和加入等操作來(lái)改變編隊(duì)隊(duì)形以適應(yīng)任務(wù)需求。將每個(gè)隊(duì)形看成系統(tǒng)的一個(gè)模態(tài),利用切換系統(tǒng)和駐留時(shí)間的方法,對(duì)具有全部穩(wěn)定模態(tài)的系統(tǒng)以及具有不穩(wěn)定模態(tài)的系統(tǒng)的穩(wěn)定性進(jìn)行研究,并通過(guò) Matlab 仿真驗(yàn)證方法的可行性。 首先,介紹了航天器編隊(duì)飛行和切換系統(tǒng)的概念,并且描述了二者之間的聯(lián)系及其研究背景和意義,針對(duì)影響航天器編隊(duì)飛行的故障種類(lèi)和容錯(cuò)方法進(jìn)行歸納,對(duì)航天器編隊(duì)飛行的研究現(xiàn)狀進(jìn)行總結(jié)。 其次,介紹幾種常用在航天器編隊(duì)運(yùn)動(dòng)的坐標(biāo)系,以四元數(shù)法描述航天器的姿態(tài),從姿態(tài)運(yùn)動(dòng)學(xué)和動(dòng)力學(xué)角度分析編隊(duì)航天器的相對(duì)運(yùn)動(dòng),針對(duì)本課題研究的一類(lèi)變組成航天器編隊(duì)飛行問(wèn)題,將整個(gè)編隊(duì)看成一個(gè)系統(tǒng),用各航天器相對(duì)于參考點(diǎn)的運(yùn)動(dòng)和姿態(tài)變量誤差作為該系統(tǒng)的狀態(tài),建立其在一般情況下的編隊(duì)飛行模型,分析系統(tǒng)的穩(wěn)定性,為下文的全穩(wěn)定模態(tài)和具有不穩(wěn)定模態(tài)下的系統(tǒng)研究奠定基礎(chǔ)。 再次,基于上述的一般模型,考慮全穩(wěn)定模態(tài)的編隊(duì)系統(tǒng)在切換瞬時(shí)狀態(tài)發(fā)生跳變,如此對(duì)整個(gè)編隊(duì)系統(tǒng)的穩(wěn)定性產(chǎn)生的影響,并將其轉(zhuǎn)化為對(duì)基于脈沖切換的編隊(duì)系統(tǒng)的穩(wěn)定性與容錯(cuò)控制的問(wèn)題的研究;針對(duì)具有不穩(wěn)定模態(tài)的編隊(duì)系統(tǒng),使用駐留時(shí)間方法,通過(guò)調(diào)節(jié)穩(wěn)定模態(tài)與不穩(wěn)定模態(tài)的激活時(shí)間的比值,利用穩(wěn)定模態(tài)來(lái)補(bǔ)償不穩(wěn)定模態(tài)的影響,從而使系統(tǒng)達(dá)到穩(wěn)定。 最后,對(duì)于基于脈沖切換的全穩(wěn)定模態(tài)和具有不穩(wěn)定模態(tài)的編隊(duì)系統(tǒng)在 Matlab 平臺(tái)上分別進(jìn)行仿真,通過(guò)仿真結(jié)果,證明了所提方法的正確性和合理性。
[Abstract]:This paper focuses on the design of fault-tolerant control for a class of variable spacecraft formation. Formation flying of spacecraft is a hot research topic in the field of spaceflight nowadays, whether for military strategy or for civilian purposes. In the face of more and more complex space tasks, a single formation can no longer meet the requirements. In order to complete a specific space mission, some spacecraft in the formation may dock and separate. Operations such as leaving and joining are used to change the formation to meet the requirements of the mission. Each formation is regarded as a mode of the system, and the method of switching the system and staying time is used. The stability of the system with all stable modes and the system with unstable mode is studied, and the feasibility of the method is verified by Matlab simulation. Firstly, the concept of spacecraft formation flying and switching system is introduced. The relationship between them and their research background and significance are described. The fault types and fault-tolerant methods affecting spacecraft formation flight are summarized, and the research status of spacecraft formation flight is summarized. This paper introduces several kinds of coordinate systems commonly used in spacecraft formation motion, describes the attitude of spacecraft by quaternion method, and analyzes the relative motion of formation spacecraft from the angle of attitude kinematics and dynamics. In view of the problem of formation flying of a class of variable composition spacecraft studied in this paper, the whole formation is regarded as a system, and the error of motion and attitude variables of each spacecraft relative to the reference point is used as the state of the system. The formation flying model under general conditions is established, and the stability of the system is analyzed, which lays a foundation for the following research on the fully stable mode and the system with unstable mode. Thirdly, based on the above general model, Considering the jump in the switching transient state of the formation system with fully stable mode, the effect on the stability of the whole formation system is considered, and the problem of the stability and fault-tolerant control of the formation system based on pulse switching is transformed into the research of the stability and fault-tolerant control of the formation system based on pulse switching. For the formation system with unstable modes, the resident time method is used to compensate the unstable modes by adjusting the ratio of the activation time of the stable mode to the unstable mode, and the stable mode is used to compensate the influence of the unstable mode by adjusting the ratio of the activation time of the stable mode to the unstable mode. Finally, the fully stable mode based on pulse switching and the formation system with unstable mode are simulated on the Matlab platform. The simulation results show that the proposed method is correct and reasonable.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類(lèi)號(hào)】：V448.2

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本文編號(hào)：1532032