Distributed optical fiber computing method for wing strain field reconstruction based on modal superposition principle

A distributed optical fiber, modal superposition technology, applied in computing, special data processing applications, electrical digital data processing, etc., can solve problems such as low accuracy and inability to accurately reconstruct strain fields.

Active Publication Date: 2019-07-26
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0005] The common algorithm for strain field reconstruction is interpolation fitting method. The interpolation fitting method is simple to calculate, but the accuracy is ...

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  • Distributed optical fiber computing method for wing strain field reconstruction based on modal superposition principle
  • Distributed optical fiber computing method for wing strain field reconstruction based on modal superposition principle
  • Distributed optical fiber computing method for wing strain field reconstruction based on modal superposition principle

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Embodiment Construction

[0056] specific implementation plan

[0057] The technical solution of the invention will be described in detail below in conjunction with the accompanying drawings: Aiming at the reconstruction of the strain field of the wing structure, a distributed optical fiber calculation method for the strain field reconstruction of the wing structure based on the principle of modal superposition is proposed. The grating sensor network measures the strain of the wing structure, and then uses the formula to derive the strain field of the wing structure.

[0058] Step 1: Based on the measurement of the strain of the wing structure of the fiber Bragg grating sensor, the strain on the surface of the wing structure is calculated by using the offset of the center wavelength of the fiber Bragg grating;

[0059] In step a, the surface strain of the wing model is measured by the fiber grating, and the central reflection wavelength of the fiber grating sensor can be expressed as:

[0060] lambda ...

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Abstract

The invention relates to a distributed optical fiber computing method for wing strain field reconstruction based on a modal superposition principle, and belongs to the field of structural health monitoring. The method comprises the following steps that 1, based on measurement of fiber grating sensor wing structure strain, calculating the strain of the surface of a wing structure through fiber grating center wavelength offset; and 2, calculating a strain mode of the wing structure, and optimizing the fiber grating sensor network layout of the wing structure through the strain mode; 3, deducinga strain matrix corresponding to the position of the measurement point of the wing structure sensor and a conversion formula between strain matrixes of all points of the wing structure; and 4, for theproblem that the strain mode matrix is uncertain, adopting a regularization method to optimize the solution of the strain mode coordinates, and reducing the strain field reconstruction error. According to the method, response signals of fiber gratings with a small number of discrete points are collected, and a wing structure strain field is deduced and calculated through a formula.

Description

technical field [0001] The invention belongs to the field of structural health monitoring, and specifically proposes a distributed optical fiber calculation method for wing structure strain field reconstruction based on the principle of modal superposition, and specifically relates to the measurement of the strain of an optical fiber grating sensor, the principle of strain modal superposition, and optical fiber grating Sensor layout optimization, etc. Background technique [0002] In structural health monitoring, strain is a very important index. Strain reflects the strength of the structure, and the failure of the structure is usually related to the strain state. By analyzing the strain of the structure, the fatigue and cracks of the structure can also be monitored. When the structure is subjected to dynamic load, it is often damaged because the strain value on the structure exceeds the limit of the structure. Real-time monitoring of the strain of the structure can well av...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F2119/18G06F30/15G06F30/23Y02T90/00
Inventor 曾捷司亚文卢李白瑜芳周智张益昕钟照振
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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