本文選題：攔截衛(wèi)星 + 執(zhí)行器故障�。� 參考：《哈爾濱工業(yè)大學(xué)》2016年碩士論文

【摘要】：隨著空間技術(shù)的發(fā)展,衛(wèi)星在現(xiàn)代信息戰(zhàn)爭(zhēng)中發(fā)揮著越來(lái)越重要的作用,為此各軍事大國(guó)均進(jìn)行了反衛(wèi)星技術(shù)研究。攔截衛(wèi)星作為一種有效的衛(wèi)星攻擊手段,一直是許多學(xué)者的研究熱點(diǎn),本文將針對(duì)攔截衛(wèi)星末段軌道的機(jī)動(dòng)控制展開(kāi)研究�？紤]到攔截衛(wèi)星發(fā)射升空后,若出現(xiàn)推進(jìn)器故障,將很難修復(fù),所以全文在控制器研究時(shí)將重點(diǎn)考慮執(zhí)行器故障的建模與容錯(cuò)補(bǔ)償設(shè)計(jì)。本文的主要研究?jī)?nèi)容可以分成四個(gè)部分:第一部分,通過(guò)對(duì)在Hill坐標(biāo)系下的牛頓動(dòng)力學(xué)微分方程進(jìn)行近似化簡(jiǎn)可以得到用于描述攔截衛(wèi)星相對(duì)軌道動(dòng)力學(xué)模型的C-W方程,在此基礎(chǔ)上,以相對(duì)速度和位置為狀態(tài)量可以得到攔截衛(wèi)星末段軌道控制的狀態(tài)空間模型,并引入軌道非圓不確定性和能量有界噪聲干擾;第二部分,考慮傳感器飽和及執(zhí)行器乘性故障設(shè)計(jì)狀態(tài)反饋控制器,在執(zhí)行器故障描述參數(shù)集已知的情況下,該控制器在滿(mǎn)足推力有限的約束下能夠使得系統(tǒng)漸近穩(wěn)定并滿(mǎn)足H_∞性能指標(biāo);第三部分,針對(duì)執(zhí)行器故障描述參數(shù)集未知的情況,結(jié)合滑�？刂频膹�(qiáng)魯棒性,設(shè)計(jì)了一種執(zhí)行器故障參數(shù)自適應(yīng)的滑模控制器,該控制器同樣能夠在滿(mǎn)足推力有限的約束下使得系統(tǒng)漸近穩(wěn)定并滿(mǎn)足H_∞性能指標(biāo);第四部分,考慮到攔截衛(wèi)星相對(duì)于目標(biāo)衛(wèi)星的位置、速度量難以實(shí)時(shí)測(cè)量得到以及執(zhí)行器加性故障的情況,設(shè)計(jì)了基于一種非脆性狀態(tài)觀測(cè)器的積分型滑模控制器,在設(shè)計(jì)過(guò)程中很好地將狀態(tài)觀測(cè)器設(shè)計(jì)與加性故障的補(bǔ)償設(shè)計(jì)融合在了一起,使得該控制器也能夠在滿(mǎn)足推力有限的約束下使得系統(tǒng)漸近穩(wěn)定并滿(mǎn)足H_∞性能指標(biāo)。本文針對(duì)三種不同情況分別提出了三種容錯(cuò)補(bǔ)償控制器設(shè)計(jì)方法,前兩種均考慮的是乘性故障,最后一種考慮的是加性故障。三種控制器設(shè)計(jì)方法均考慮了軌道的非圓不確定性、能量有界噪聲干擾及推力有限條件,不同的是分別引入了傳感器飽和、執(zhí)行器故障參數(shù)自適應(yīng)估計(jì)以及狀態(tài)觀測(cè)器。另外,滑�？刂评碚摰膽�(yīng)用使得后兩種控制器在應(yīng)對(duì)模型不確定性、參數(shù)不確定性及外部干擾時(shí)具有更好的魯棒性。
[Abstract]:With the development of space technology, satellites play a more and more important role in modern information warfare. As an effective means of satellite attack, interceptor satellite has been a hot research topic of many scholars. In this paper, the maneuvering control of the terminal orbit of intercepting satellite will be studied. Considering that after launching the interceptor satellite, it will be very difficult to repair the fault of the thruster, so in the research of the controller, the modeling of the actuator fault and the design of fault tolerance compensation will be considered in this paper. The main research contents of this paper can be divided into four parts: in the first part, the C-W equation used to describe the dynamic model of the relative orbit of the interceptor satellite can be obtained by approximate simplification of the Newtonian dynamical differential equation in the Hill coordinate system. On this basis, the state space model of the terminal orbit control of the interceptor satellite can be obtained by taking the relative velocity and position as the state variables, and the orbit non-circular uncertainty and the energy bounded noise disturbance can be introduced. Considering the sensor saturation and actuator multiplicative fault design state feedback controller, when the actuator fault description parameter set is known, The controller can make the system asymptotically stable and satisfy the H _ 鈭，

本文編號(hào)：1970720