本文選題：光纖光柵 + 啁啾效應(yīng)　； 參考：《南京航空航天大學(xué)》2017年碩士論文

【摘要】：隨著航空航天復(fù)合材料結(jié)構(gòu)的大型化、復(fù)雜化和任務(wù)模式多元化發(fā)展,其在服役期間將不可避免地受到多種復(fù)雜環(huán)境因素的影響,這勢必會導(dǎo)致結(jié)構(gòu)可靠性大幅下降。航空航天復(fù)合材料結(jié)構(gòu)健康狀態(tài)很大程度上與其所受熱載荷響應(yīng)特性密切相關(guān),因此,本文基于光纖傳感技術(shù)分別對典型航空航天復(fù)合材料結(jié)構(gòu)的溫度、熱應(yīng)變、熱屬性監(jiān)測方法展開研究,為結(jié)構(gòu)服役安全狀態(tài)的評估提供依據(jù)。主要工作包括以下幾個方面:首先,理論分析了光纖光柵傳感器傳感機(jī)理,并從數(shù)值仿真和實驗不同角度研究了不同溫度、應(yīng)變下光纖光柵傳感器的響應(yīng)光譜特性,研究并驗證了光纖光柵低溫啁啾效應(yīng)的形成機(jī)理。其次,提出了一種管式光纖光柵溫度傳感器的封裝方法,并針對不同的使用工況,研究了打孔型管式封裝光纖光柵溫度傳感器。在此基礎(chǔ)上,探究了在不同封裝形式下光纖光柵傳感器的溫度感知特性。再次,選取碳纖維圓筒結(jié)構(gòu)、碳纖維實心桿結(jié)構(gòu)為研究對象,構(gòu)建了基于分布式光纖光柵傳感網(wǎng)絡(luò)的復(fù)合材料結(jié)構(gòu)熱應(yīng)變測試系統(tǒng),并分析了光纖光柵傳感器與電阻應(yīng)變片同時對結(jié)構(gòu)進(jìn)行熱應(yīng)變監(jiān)測時的測試誤差。接著,構(gòu)建了碳纖維蜂窩夾芯結(jié)構(gòu)熱載荷測試系統(tǒng),研究了高低溫?zé)彷d荷下植入試件不同鋪層位置的光纖光柵傳感器反射光譜響應(yīng)特征;提出一種基于表貼式光纖光柵力學(xué)模型的復(fù)合材料板結(jié)構(gòu)熱膨脹系數(shù)計算方法,并通過數(shù)值仿真驗證了方法的可行性。最后,構(gòu)建了基于LabVIEW的光纖光柵硬件測試系統(tǒng),提出了光纖光柵多參量監(jiān)測系統(tǒng)軟件的功能需求以及框架方案,設(shè)計并實現(xiàn)了光纖光柵多參量監(jiān)測系統(tǒng)主程序,同時完成人機(jī)交互界面的設(shè)計。
[Abstract]:With the development of large-scale, complex and mission mode of aerospace composite structure, it will inevitably be affected by a variety of complex environmental factors during service, which will inevitably lead to a large decline in structural reliability. The health state of aerospace composite structures is closely related to the response characteristics of thermal loads. Therefore, the temperature and thermal strain of typical aerospace composite structures are studied based on optical fiber sensing technology. The thermal attribute monitoring method is studied to provide the basis for the evaluation of the safety state of the structure in service. The main work includes the following aspects: firstly, the sensing mechanism of fiber grating sensor is analyzed theoretically, and the response spectrum characteristics of fiber grating sensor under different temperature and strain are studied from different angles of numerical simulation and experiment. The formation mechanism of low temperature chirp effect of fiber gratings is studied and verified. Secondly, an encapsulation method of tubular fiber Bragg grating temperature sensor is proposed, and the perforated tube packaged fiber grating temperature sensor is studied according to different operating conditions. On this basis, the temperature sensing characteristics of fiber Bragg grating sensors in different packaging forms are investigated. Thirdly, the structure of carbon fiber cylinder and solid rod of carbon fiber is selected as the research object, and the thermal strain measurement system of composite structure based on distributed fiber grating sensor network is constructed. The measurement error of fiber grating sensor and resistance strain gauge for thermal strain monitoring of the structure is analyzed. Then, the thermal load measurement system of carbon fiber honeycomb sandwich structure is constructed, and the reflection spectrum response characteristics of fiber Bragg grating sensors with different layering positions are studied under high and low temperature thermal loads. A method for calculating the thermal expansion coefficient of composite plate structure based on the mechanical model of surface fiber Bragg grating is proposed. The feasibility of the method is verified by numerical simulation. Finally, the hardware testing system of fiber Bragg grating based on LabVIEW is constructed. The function requirement and frame scheme of fiber grating multi-parameter monitoring system software are put forward, and the main program of fiber Bragg grating multi-parameter monitoring system is designed and realized. At the same time, the design of man-machine interface is completed.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2017
【分類號】：TP212;TP274

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本文編號：2080872