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Plate structure deformation distributed optical fiber calculation method based on double integrating principle and application thereof

A distributed optical fiber, double integration technology, applied in the direction of using optical devices, measuring devices, instruments, etc., can solve the problems of gaps between the grid area and the substrate, affecting the strain transfer coefficient of the sensor, etc.

Active Publication Date: 2016-02-24
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

Considering that the traditional fiber grating pasting method cannot guarantee the close contact between the sensor and the structural substrate, it is easy to cause a gap between the grid area and the substrate. The strain transfer coefficient between the three sensors

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  • Plate structure deformation distributed optical fiber calculation method based on double integrating principle and application thereof
  • Plate structure deformation distributed optical fiber calculation method based on double integrating principle and application thereof
  • Plate structure deformation distributed optical fiber calculation method based on double integrating principle and application thereof

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Embodiment Construction

[0025] According to the mechanics of materials and the principle of fiber grating sensors, the center wavelength offsets of the fiber grating sensors pasted on different positions of the plate structure in the fiber sensor array are converted into corresponding curvature values, and the curvature information matrix is ​​constructed on this basis.

[0026] As attached in the manual figure 2 As shown, assume that the length of the surface microelement is L, the height is h, the stretching amount of a certain layer of the surface microelement is ΔL, and the radius of curvature of the curved surface microelement is ρ, assuming that the neutral plane remains unchanged. According to the plane assumption, the two cross-sections whose distance is L before deformation, respectively rotate around the neutral axis by an angle dθ / 2 after deformation, and remain as planes. It can be known from the geometrical characteristics of microelements that:

[0027] c'd'=(ρ+y)dθ(1)

[0028] It is...

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Abstract

The invention relates to a plate structure deformation distributed optical fiber calculation method based on a double integrating principle and an application thereof, and the method is similar to the plate structure deformation optical calculation technology of a wing. The method specifically comprises a structure deformation calculation inverse algorithm of fiber grating sensors, a fiber grating sensor layout optimization method and a glued joint method between the fiber grating sensors and a plate structure. The invention provides the plate structure deformation distributed optical fiber calculation method based on the double integrating principle, the number of the fiber grating sensors used in the deformation calculation is reduced, the deformation calculation algorithm is simplified, the calculation amount is reduced, and the pasting performance between the fiber grating sensors and the plate structure is improved, so that the purpose that the fiber grating sensors precisely measure the deformation is achieved.

Description

technical field [0001] The invention belongs to the field of optical fiber intelligent monitoring, and specifically relates to a double integral calculation algorithm of structural deformation based on an optical fiber grating sensor, optimization of the layout of the optical fiber grating sensor, improvement of the integration method of the grating sensor and the board structure, and the like. Background technique [0002] Deformation monitoring is one of the important parameter calculations in the field of aerospace. Conventional deformation monitoring methods are mainly based on electrical measurement and digital photography. Generally, methods such as displacement meters, resistance changes, total stations, and GPS are used. The main implementation form of monitoring. Due to the limitation of monitoring principles, such as GPS, total station, subsidence instrument, inclinometer, etc. are difficult to be used for real-time measurement of aerospace vehicles during service,...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01B11/16
CPCG01B11/165
Inventor 曾捷张钰珏李钰王晓钢李丹婷梁大开康健
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS