变构型飞行器蒙皮多维大尺度变形重构方法

变构型飞行器在执行不同飞行任务时会大尺度地改变机翼结构和蒙皮形状，蒙皮多维大尺度的变形重构是变形飞行器研究中的难点。本文针对这一问题，提出一种基于多芯光纤传感的变形飞行器蒙皮变形形状重构方法。该方法基于多芯光纤光栅应变传感原理，利用传感器上的多个光栅传感点，建立光栅波长漂移和曲率之间的转换关系，实现三维曲线重构。此外，为了重构变构型飞行器多维大尺度变形下的形状，本文研究了将重构曲线转化为飞行器机翼的展开角和翻转角，并结合两个角度和飞行器机翼的长宽等固有参数，通过拟合插值将两个角度变化引起的变形连续化，实现了柔性蒙皮多维大尺度变形重构。同时，本文为了减小温度造成的误差，利用多芯光纤中间纤芯不受拉伸和压缩、只受温度影响的特点，将中间纤芯与旁轴纤芯的中心波长漂移量做差，实现温度解耦。为了验证本文变形重构方法的有效性，对飞行器蒙皮多种不同情况下的变形进行了实验测试，并将形变重构结果与视觉测量进行了对比。研究结果表明，飞行器蒙皮多维大尺度变形重构的平均误差为7 mm,变形角度重构的平均误差为3.6%,可以实现变构型飞行器蒙皮多维大尺度变形重构，该方法在航空航天器等结构变形监测领域具有良好的应用前...

Variant aircraft skin multidimensional large-scale deformation reconstruction method

The variant aircraft will change the wing structure and skin shape on a large scale when performing different flight tasks. Thelarge-scale deformation reconstruction of the skin multi-dimensional is a difficult point in the research of deformed aircraft. To solve thisproblem, this article proposes a deformed shape reconstruction method for the deformed aircraft skin based on multi-core optical fibersensing. Based on the principle of multi-core fiber grating strain sensing, this method uses multiple grating sensing points on the sensorto establish the conversion relationship between grating wavelength drift and curvature, which realizes three-dimensional curvereconstruction. In addition, to reconstruct the shape under the multi-dimensional large-scale deformation of the variable configurationaircraft, this article studies the transformation of the reconstruction curve into the unfolding angle and flip angle of the aircraft wing, andcombines the inherent parameters such as the two angles and the length and width of the aircraft wing, and continuously integrates thedeformation caused by the change of the two angles by fitting the interpolation, so as to realize the multi-dimensional large-scaledeformation reconstruction of flexible skin. Meanwhile, to reduce the error caused by temperature, this article uses the characteristicsthat the intermediate fiber core of multi-core fiber is not stretched and compressed, and is only affected by temperature, and the center wavelength drift of the intermediate fiber core and the side shaft core is differentiated, so as to realize temperature decoupling. To evaluatethe effectiveness of the proposed deformation reconstruction method, the deformation of the aircraft skin under different conditions isexperimentally tested, and the deformation reconstruction results are compared with visual measurements. The results show that the averageerror of multi-dimensional large-scale deformation reconstruction of aircraft skin is 7 mm, and the average error of deformation anglereconstruction is 3. 6% , which can realize multi-dimensional large-scale deformation reconstruction of modified configuration aircraft, andthis method has good application prospects in the field of structural deformation monitoring such as aerospace vehicles.