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Composite material laminate optical fiber impact position identification method based on strain nonlinear weighting

A non-linear weighting and composite material layer technology, which is applied in the direction of analyzing materials, using one-time impact force to test the strength of materials, measuring devices, etc., can solve the problems of susceptibility to electromagnetic interference and cumbersome process, and achieve strong anti-electromagnetic interference ability and processing Simple, simple layout effect

Active Publication Date: 2021-06-29
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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Problems solved by technology

[0006] Purpose of the invention: Aiming at the deficiencies such as high-speed demodulation equipment required by the time difference positioning method for piezoelectric sensors, which are susceptible to electromagnetic interference; pattern recognition methods for FBG sensors require a large amount of prior knowledge, and the process is cumbersome; the invention provides a composite material plate structure Shock load position identification method based on

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  • Composite material laminate optical fiber impact position identification method based on strain nonlinear weighting
  • Composite material laminate optical fiber impact position identification method based on strain nonlinear weighting
  • Composite material laminate optical fiber impact position identification method based on strain nonlinear weighting

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Embodiment Construction

[0043] The technical solution of the present invention will be further described in detail below in conjunction with the accompanying drawings.

[0044] Step 1: OFDR distributed fiber optic sensor network layout

[0045] Step a: Construct a square monitoring area ABCD at the center of the four-sided fixed-supported composite plate structure, where point A is located in the upper left corner, and points A, B, C, and D are the vertices of the square arranged in a clockwise direction; a two-dimensional right-angle Coordinate system, select the central position of the area to be monitored of the composite material plate structure as the coordinate origin O, define the X axis parallel to the AB direction, and the Y axis parallel to the AD direction;

[0046] Step b: Select three rows of OFDR distributed optical fiber sensor paste paths parallel to the X-axis direction in the monitoring area, and name them as the first, second, and third row of sensor paths from bottom to top. The f...

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Abstract

The invention discloses a composite material laminate optical fiber impact position identification method based on strain nonlinear weighting, and belongs to the technical field of structural health monitoring. The method comprises the following steps of 1, arranging an OFDR distributed optical fiber sensor network; 2, acquiring an impact load response signal of an OFDR distributed optical fiber sensor; 3, according to a stress concentration phenomenon at the impact load acting point of a composite material plate structure, extracting a strain amplitude feature vector; 4, constructing a to-be-positioned sensing area through the strain amplitude feature vector; 5, establishing a strain amplitude nonlinear weighted centroid positioning functional expression, and solving to obtain an impact load positioning coordinate; and 6, optimizing and selecting nonlinear weighting times m by taking the minimum target function value of the positioning error of the sample impact point as a criterion, and recalculating the prediction coordinate of the impact point. The method is simple, convenient and high in practicability.

Description

technical field [0001] The invention belongs to the technical field of load monitoring for structural health monitoring, and specifically proposes a method for identifying the impact load position of a composite material laminate optical fiber based on strain nonlinear weighting. Background technique [0002] Composite plate structure has been widely used in the aerospace field due to its high specific strength and specific stiffness, good fatigue resistance and durability. However, aerospace vehicles are vulnerable to impacts from external objects such as bird strikes, space debris, runway flying rocks, bullet strikes, and hailstones during their service. The damage caused by impact to the composite plate structure is usually sudden, especially some low-energy low-speed impacts. Although no traces are left on the surface of the object, it will cause microcracks, delamination and fiber breakage inside the composite material structure. Such as visually undetectable damage fo...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/30G01N3/06G06F30/20
CPCG01N3/30G01N3/068G06F30/20G06F2113/26
Inventor 曾捷钟照振冯振辉严桢锋吴亚星王云嵩孙阳阳綦磊
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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