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》2016年碩士論文

【摘要】：隨著空間技術的發(fā)展,衛(wèi)星在現代信息戰(zhàn)爭中發(fā)揮著越來越重要的作用,為此各軍事大國均進行了反衛(wèi)星技術研究。攔截衛(wèi)星作為一種有效的衛(wèi)星攻擊手段,一直是許多學者的研究熱點,本文將針對攔截衛(wèi)星末段軌道的機動控制展開研究。考慮到攔截衛(wèi)星發(fā)射升空后,若出現推進器故障,將很難修復,所以全文在控制器研究時將重點考慮執(zhí)行器故障的建模與容錯補償設計。本文的主要研究內容可以分成四個部分:第一部分,通過對在Hill坐標系下的牛頓動力學微分方程進行近似化簡可以得到用于描述攔截衛(wèi)星相對軌道動力學模型的C-W方程,在此基礎上,以相對速度和位置為狀態(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)行器乘性故障設計狀態(tài)反饋控制器,在執(zhí)行器故障描述參數集已知的情況下,該控制器在滿足推力有限的約束下能夠使得系統(tǒng)漸近穩(wěn)定并滿足H_∞性能指標;第三部分,針對執(zhí)行器故障描述參數集未知的情況,結合滑模控制的強魯棒性,設計了一種執(zhí)行器故障參數自適應的滑�？刂破�,該控制器同樣能夠在滿足推力有限的約束下使得系統(tǒng)漸近穩(wěn)定并滿足H_∞性能指標;第四部分,考慮到攔截衛(wèi)星相對于目標衛(wèi)星的位置、速度量難以實時測量得到以及執(zhí)行器加性故障的情況,設計了基于一種非脆性狀態(tài)觀測器的積分型滑模控制器,在設計過程中很好地將狀態(tài)觀測器設計與加性故障的補償設計融合在了一起,使得該控制器也能夠在滿足推力有限的約束下使得系統(tǒng)漸近穩(wěn)定并滿足H_∞性能指標。本文針對三種不同情況分別提出了三種容錯補償控制器設計方法,前兩種均考慮的是乘性故障,最后一種考慮的是加性故障。三種控制器設計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)行器故障參數自適應估計以及狀態(tài)觀測器。另外,滑�？刂评碚摰膽檬沟煤髢煞N控制器在應對模型不確定性、參數不確定性及外部干擾時具有更好的魯棒性。
[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：1970720