植入碳纤维蜂窝夹芯结构的光纤光栅热载荷响应光谱研究

发布时间：2018-05-30 18:34

本文选题：碳纤维蜂窝夹芯结构 + 光纤光栅　；参考：《光谱学与光谱分析》2017年09期

【摘要】：针对航天领域复合材料结构在空间服役环境的热响应监测需求,研究了一种热载荷作用下基于光纤Bragg光栅(FBG)反射光谱特征分析的碳纤维蜂窝夹芯结构监测方法。将光纤Bragg光栅传感器分别植入碳纤维蜂窝夹芯结构的不同铺层,通过监测不同热载荷下各铺层位置的光纤光栅反射光谱,得到碳纤维蜂窝夹芯结构相关铺层位置热应变特征。研究表明,碳纤维蜂窝夹芯结构不同材料铺层的热应变特征存在一定差异。植入外蒙皮表面与玻璃布之间的光纤光栅反射光谱随着温度升高,中心波长向长波方向漂移,且波形未出现明显改变。埋植于外蒙皮第二、三层碳纤维织物预浸料之间的光栅反射光谱随着温度降低逐渐出现旁瓣、多峰等啁啾效应,其主峰与右侧次峰中心波长均向短波方向逐渐漂移,主峰峰值幅度变化较小,温度灵敏度约为5.56×10~(-3) dBm·℃~(-1),而右侧次峰幅度显著增大,温度灵敏度约为40.32×10~(-3)dBm·℃~(-1);埋植于内蒙皮和蜂窝芯子之间的光栅反射光谱随着温度降低,其半波峰带宽逐渐增大,变化率约为3.19pm·℃~(-1),且出现显著多峰趋势,这是由于层间热应力分布不均匀所形成。在-70~+60℃温度范围,各植入层热应变均随温度升高而增大,且变化趋势相接近,而在+60~+120℃温度范围内,各植入层热应变变化趋势呈现显著差异。这些特性能够为后继空间环境复合材料航天器结构状态在轨监测提供有益帮助。
[Abstract]:In view of the thermal response monitoring requirement of space service structure in space service environment, a monitoring method of carbon fiber honeycomb sandwich structure based on optical fiber Bragg grating (FBG) reflection spectrum characteristic analysis under thermal load is studied. Fiber Bragg grating sensors are implanted into different layers of carbon fiber honeycomb sandwich structure. The thermal strain characteristics of the related layer of carbon fiber honeycomb sandwich structures are obtained by monitoring the fiber Bragg grating reflectance spectra at different thermal loads at different thermal loads. The study shows that there is a certain difference in the thermal strain characteristics of the layers of carbon fiber honeycomb sandwich structures. The fiber Bragg grating reflectance spectra between the surface of the outer skin and the glass cloth As the temperature rises, the central wavelength shifts to the direction of the long wave, and the waveform does not change obviously. The grating reflection spectrum embedded in the second, third layer carbon fiber fabric prepreg of the outer skin gradually appears as the side lobe and multi peak chirp effect, and the main peak and the right sub peak center wavelength shift gradually to the short wave direction, the main peak of the main peak and the main peak. The variation of the peak amplitude is small, the temperature sensitivity is about 5.56 x 10~ (-3) dBm. C ~ (-1), and the right sub peak amplitude increases significantly, the temperature sensitivity is about 40.32 x 10~ (-3) dBm. C ~ (-1). The grating reflection spectrum embedded between the Inner Mongolia skin and the honeycomb core decreases with the temperature, and the half wave peak bandwidth increases gradually, the change rate is about 3.19pm. C ~ (-1). There is a significant multi peak trend, which is due to the uneven distribution of thermal stress in the interlayer. At -70~+60 C, the thermal strain of each layer increases with the increase of temperature, and the change trend is close. In the range of +60~+120 C, the changes of the thermal strain of each implant show a significant difference. These characteristics can be the following space. Environmental composite spacecraft structure monitoring provides useful help in orbit monitoring.
【作者单位】：南京航空航天大学机械结构力学及控制国家重点实验室;中国航天科技集团公司北京卫星环境工程研究所;Université
【基金】：国家自然科学基金-联合基金项目(U1537102) CAST-BISEE基金项目航空科学基金项目(20152852036) 江苏省产学研联合创新资金项目(BY2014003-01) 中央高校基本科研业务费专项资金项目(NS2016004) 机械结构力学及控制国家重点实验室开放课题(MCMS-0516K01) 江苏高校优势学科建设工程基金项目资助
【分类号】：TN253

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