光纤光栅低温特性及复合材料结构热属性监测方法研究

发布时间：2018-06-29 04:36

本文选题：光纤光栅 + 啁啾效应　；参考：《南京航空航天大学》2017年硕士论文

【摘要】：随着航空航天复合材料结构的大型化、复杂化和任务模式多元化发展,其在服役期间将不可避免地受到多种复杂环境因素的影响,这势必会导致结构可靠性大幅下降。航空航天复合材料结构健康状态很大程度上与其所受热载荷响应特性密切相关,因此,本文基于光纤传感技术分别对典型航空航天复合材料结构的温度、热应变、热属性监测方法展开研究,为结构服役安全状态的评估提供依据。主要工作包括以下几个方面:首先,理论分析了光纤光栅传感器传感机理,并从数值仿真和实验不同角度研究了不同温度、应变下光纤光栅传感器的响应光谱特性,研究并验证了光纤光栅低温啁啾效应的形成机理。其次,提出了一种管式光纤光栅温度传感器的封装方法,并针对不同的使用工况,研究了打孔型管式封装光纤光栅温度传感器。在此基础上,探究了在不同封装形式下光纤光栅传感器的温度感知特性。再次,选取碳纤维圆筒结构、碳纤维实心杆结构为研究对象,构建了基于分布式光纤光栅传感网络的复合材料结构热应变测试系统,并分析了光纤光栅传感器与电阻应变片同时对结构进行热应变监测时的测试误差。接着,构建了碳纤维蜂窝夹芯结构热载荷测试系统,研究了高低温热载荷下植入试件不同铺层位置的光纤光栅传感器反射光谱响应特征;提出一种基于表贴式光纤光栅力学模型的复合材料板结构热膨胀系数计算方法,并通过数值仿真验证了方法的可行性。最后,构建了基于LabVIEW的光纤光栅硬件测试系统,提出了光纤光栅多参量监测系统软件的功能需求以及框架方案,设计并实现了光纤光栅多参量监测系统主程序,同时完成人机交互界面的设计。
[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.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2017
【分类号】：TP212;TP274

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