【摘要】：應(yīng)變、變形、振動(dòng)監(jiān)測(cè)與控制是航空航天領(lǐng)域的研究基礎(chǔ),是不可或缺的部分。對(duì)結(jié)構(gòu)的應(yīng)變變形準(zhǔn)確的監(jiān)測(cè),是進(jìn)行航空航天結(jié)構(gòu)參數(shù)后續(xù)測(cè)量的前提。因此本文對(duì)復(fù)合材料板和機(jī)翼結(jié)構(gòu)進(jìn)行變形重構(gòu)分析,主要包括以下幾個(gè)方面:首先,基于應(yīng)變傳遞理論,提出一種改進(jìn)型光纖光柵傳感器與復(fù)合材料集成方法。并通過(guò)理論與試驗(yàn)同時(shí)驗(yàn)證改進(jìn)型光纖光柵的集成方法具有良好的應(yīng)變監(jiān)測(cè)效果,證明本文討論的光纖光柵傳感器與復(fù)合材料的集成方法具有良好的工程實(shí)用意義。其次,討論了一種基于分布式光纖光柵傳感網(wǎng)絡(luò)的應(yīng)變信息曲率信息轉(zhuǎn)換關(guān)系的變形重構(gòu)方法和基于雙重積分方法的變形重構(gòu)方法。在仿真的基礎(chǔ)上,對(duì)單邊固支環(huán)氧板進(jìn)行了均布加載實(shí)驗(yàn),利用光纖光柵傳感器監(jiān)測(cè)數(shù)據(jù)重構(gòu)變形位移。再次,在機(jī)翼結(jié)構(gòu)模型上設(shè)計(jì)了4種加載方式,分別表示彎曲與扭轉(zhuǎn)情況。利用光纖光柵傳感器測(cè)得的波長(zhǎng)信息轉(zhuǎn)化為監(jiān)測(cè)點(diǎn)的曲率信息,并利用曲率信息重構(gòu)不同加載情況下的變形。利用正交方向上的曲率信息擬合機(jī)翼結(jié)構(gòu)的變形曲面片重構(gòu),并展示了曲面重構(gòu)過(guò)程,最后對(duì)變形重構(gòu)進(jìn)行了均方根誤差分析。利用粘貼于機(jī)翼翼面上的加速度傳感器大致估計(jì)出機(jī)翼結(jié)構(gòu)的模態(tài)固有頻率。之后利用光纖光柵傳感器測(cè)得的波長(zhǎng)信息與激振力之間的頻響函數(shù),求出該機(jī)翼的模態(tài)參數(shù)。
[Abstract]:Strain, deformation, vibration monitoring and control are the basic and indispensable part of aerospace research. Accurate monitoring of structural strain deformation is the prerequisite for subsequent measurement of aerospace structure parameters. Therefore, the deformation reconstruction analysis of composite plate and wing structure is carried out in this paper, including the following aspects: firstly, based on the strain transfer theory, an improved method of integrating fiber Bragg grating sensors with composite materials is proposed. At the same time, both theoretical and experimental results show that the improved method has good strain monitoring effect, which proves that the integrated method of fiber Bragg grating sensor and composite material discussed in this paper has good practical significance in engineering. Secondly, a deformation reconstruction method based on the transformation of curvature information of strain information based on distributed fiber Bragg grating sensor network and a deformation reconstruction method based on double integral method are discussed. On the basis of simulation, the uniform loading experiment of single-side clamped epoxy plate was carried out, and the deformation displacement was reconstructed by using fiber Bragg grating sensor. Thirdly, four loading modes are designed on the wing structure model to represent bending and torsion respectively. The wavelength information measured by fiber Bragg grating sensor is converted into the curvature information of monitoring points, and the deformation under different loading conditions is reconstructed by using the curvature information. The curvature information in orthogonal direction is used to fit the deformation surface reconstruction of wing structure, and the process of surface reconstruction is demonstrated. Finally, the root mean square error analysis of deformation reconstruction is carried out. The modal natural frequency of the wing structure is estimated by the acceleration sensor affixed to the wing surface. Then the modal parameters of the wing are obtained by using the frequency response function between the wavelength information and the exciting force measured by the fiber grating sensor.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2016
【分類(lèi)號(hào)】：V216
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本文編號(hào)：2378878