本文選題：衛(wèi)星姿態(tài)控制 + 可重構性　； 參考：《南京航空航天大學》2015年碩士論文

【摘要】：姿態(tài)控制系統(tǒng)是衛(wèi)星的關鍵分系統(tǒng),其可靠性和壽命對整個衛(wèi)星的運行具有重要意義。本文針對衛(wèi)星姿態(tài)控制系統(tǒng),對系統(tǒng)可重構性以及系統(tǒng)的剩余壽命預測方法進行了研究,并在此基礎上,考慮系統(tǒng)可重構性對衛(wèi)星姿態(tài)控制系統(tǒng)剩余壽命的影響,研究該情況下的衛(wèi)星姿態(tài)控制系統(tǒng)剩余壽命預測方法。在對衛(wèi)星姿態(tài)控制系統(tǒng)模型和系統(tǒng)組成介紹的基礎上,研究了衛(wèi)星姿態(tài)控制系統(tǒng)的可重構性:首先定義了衛(wèi)星姿態(tài)控制系統(tǒng)可重構性的概念,針對衛(wèi)星姿態(tài)控制系統(tǒng)執(zhí)行器分系統(tǒng)和傳感器分系統(tǒng),分別定義了可重構性判據(jù),并基于控制能耗定義了系統(tǒng)的可重構性度量指標,還針對三正一斜裝飛輪和四斜裝飛輪配置分別進行了可重構性仿真與分析。針對衛(wèi)星姿態(tài)控制系統(tǒng)剩余壽命預測方法的研究,充分考慮系統(tǒng)組成和系統(tǒng)故障對系統(tǒng)剩余壽命的影響,在對系統(tǒng)組成分析的基礎上,定義系統(tǒng)的故障狀態(tài),并通過Kaplan Meier估計器和極大似然估計法對系統(tǒng)故障狀態(tài)間轉移概率模型進行估計,建立衛(wèi)星姿態(tài)控制系統(tǒng)的Petri網模型,對Petri網模型進行大量仿真便可實現(xiàn)對衛(wèi)星姿態(tài)控制系統(tǒng)剩余壽命的預測。系統(tǒng)可重構性是衛(wèi)星姿態(tài)控制系統(tǒng)的一個重要性質,也是系統(tǒng)剩余壽命一個重要影響因素,因而基于可重構性對衛(wèi)星姿態(tài)控制系統(tǒng)的剩余壽命預測方法進行研究具有重要的意義。由于執(zhí)行機構的可重構性判據(jù)中涉及到了系統(tǒng)控制能耗,而系統(tǒng)控制能耗的計算需要知道飛輪的有效因子,首先根據(jù)飛輪部件的轉速、軸溫、電流等數(shù)據(jù)信息和模糊推理方法確定飛輪部件的有效因子,然后對系統(tǒng)的控制能耗進行計算并對系統(tǒng)進行可重構性分析,最后,在此基礎上對系統(tǒng)進行故障狀態(tài)定義,建立衛(wèi)星姿態(tài)控制系統(tǒng)的剩余壽命預測模型,從而實現(xiàn)對考慮可重構性情況下的衛(wèi)星姿態(tài)控制系統(tǒng)剩余壽命的預測,并針對具體的衛(wèi)星姿態(tài)控制系統(tǒng)配置進行了仿真驗證。
[Abstract]:Attitude control system is the key subsystem of satellite, and its reliability and lifetime are of great significance to the operation of the whole satellite. In this paper, the reconfiguration of the satellite attitude control system and the residual life prediction method of the system are studied. On this basis, the influence of the reconfiguration of the system on the residual life of the satellite attitude control system is considered. The residual life prediction method of satellite attitude control system is studied in this paper. Based on the introduction of satellite attitude control system model and system composition, the reconfiguration of satellite attitude control system is studied. Firstly, the concept of satellite attitude control system reconfiguration is defined. For satellite attitude control system actuator subsystem and sensor subsystem, reconfigurable criteria are defined, and reconfigurable metrics are defined based on control energy consumption. The reconfigurable simulation and analysis of three straight and one oblique flywheel and four oblique flywheel configuration are also carried out. In view of the research of residual life prediction method of satellite attitude control system, the influence of system composition and system fault on system residual life is fully considered. Based on the analysis of system composition, the fault state of the system is defined. The system transition probability model is estimated by Kaplan Meier estimator and maximum likelihood estimation method, and the Petri net model of satellite attitude control system is established. The residual life of satellite attitude control system can be predicted by a lot of simulation on Petri net model. The reconfiguration of the system is an important property of the satellite attitude control system, and it is also an important influence factor of the residual life of the system. Therefore, it is of great significance to study the residual life prediction method of satellite attitude control system based on reconfiguration. Since the system control energy consumption is involved in the reconfiguration criterion of the actuator, and the calculation of the system control energy consumption needs to know the effective factor of the flywheel, firstly, according to the speed of the flywheel component, the temperature of the shaft, Current and other data information and fuzzy inference method are used to determine the effective factors of flywheel components. Then the control energy consumption of the system is calculated and the reconfiguration of the system is analyzed. Finally, the fault state of the system is defined on this basis. The residual life prediction model of satellite attitude control system is established to predict the residual life of satellite attitude control system considering reconfiguration, and the simulation verification is carried out for the configuration of satellite attitude control system.
【學位授予單位】：南京航空航天大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：V448.22

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