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Method for monitoring impact threats of composite material part structure in non-interference mode

A technology for composite materials and parts, which is applied in the field of non-interference monitoring of impact threats to the structure of composite parts. It can solve the problems of reducing the structural performance of composite materials, achieve the integration of structure and function, and improve the level of shock warning and technical value. Effect

Inactive Publication Date: 2012-07-11
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the huge difference between the grating fiber and the fiber used to reinforce the structural composite material in terms of geometric size and physical properties, the grating fiber embedded in the high-performance structural composite material layup will seriously reduce the structural performance of the composite material, resulting in the so-called "structural interference". effect, therefore, in structural performance analysis, buried grating fibers are usually treated as "defects"

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] The grating optical fiber is embedded in the connection area between the ribs and the bottom plate of the reinforced panel formed by the secondary bonding of the CCF300 / 5228A autoclave to realize the impact threat perception function of the panel. The specific steps are:

[0028] (1) Select five grating fibers with a diameter of 100 μm and a grating pitch of 100 mm, soak them in acetone for 4 hours, remove the pollutants remaining on the surface of the grating fibers, and treat them in a vacuum oven at 80°C for 2 hours before use;

[0029] (2) Straighten the five grating optical fibers to be used and roll them into the CCF300 / 5228A prepreg to form the filler in the filling area of ​​the stiffened surface. The theoretical fiber volume fraction of the filler is (60±3)%. At the same time Add a polytetrafluoroethylene protective sleeve with a lumen diameter greater than 150 μm on the exposed optical fiber;

[0030] (3) After curing the filler and ribs in (2) once, use SY-1...

Embodiment 2

[0033] The grating optical fiber is embedded in the asymmetric connection area of ​​the T700 / 5228E co-cured capped wall panel to realize the impact threat perception function of the wall panel. The specific steps are:

[0034] (1) Select six grating fibers with a diameter of 125 μm and a grating pitch of 85 mm, soak them in acetone for 4 hours, remove the pollutants remaining on the surface of the grating fibers, and treat them in a vacuum oven at 80°C for 2 hours before use;

[0035](2) After straightening the six grating optical fibers to be used, use a special mold to roll into the T700 / 5228E prepreg to form the filler in the filling area of ​​the stiffened surface. The theoretical fiber volume fraction of the filler is (60±3)% , while adding a polytetrafluoroethylene protective sheath with an inner cavity diameter greater than 200 μm on the exposed optical fiber;

[0036] (3) Assemble the filler, hat-shaped ribs and panels in (2) after pre-curing at 120°C / 60min, and then ...

Embodiment 3

[0039] The grating optical fiber is embedded in the asymmetric and symmetrical connection areas of the T800 / 5228A co-cemented composite reinforced wall panel to realize the impact threat perception function of the wall panel. The specific steps are:

[0040] (1) Select three grating fibers with a diameter of 100 μm and a grating pitch of 70 mm, soak them in acetone for 4 hours, remove the pollutants remaining on the surface of the grating fibers, and treat them in a vacuum oven at 80°C for 2 hours before use;

[0041] (2) After straightening the three ready-to-use grating optical fibers, use a special mold to roll into the T800 / 5228A prepreg to form the filler in the filling area of ​​the L-shaped stringer and the T-shaped second and third walls. The theory of the filler The fiber volume fraction is (60±3)%, and at the same time add a polytetrafluoroethylene protective sleeve with a lumen diameter greater than 150 μm on the exposed optical fiber;

[0042] (3) Pre-cure the fil...

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Abstract

The invention belongs to the technical field of composite material functionalization, and relates to a method for monitoring impact threats of a composite material part structure in a non-interference mode. Under the premise that the performance of a composite material structure is not influenced at all, and functionalization dynamic sensing grating optical fibers are embedded in a non-interference area of a composite material product structure, so that whether the composite material section bar or the part structure suffers from impacts or not and positions suffering from the impacts are monitored on line with whole service life and low cost, structure safety alert level of the composite material or the part in a key application site is improved, and real-time examinability and structural reliability of impact damage are improved.

Description

technical field [0001] The invention belongs to the technical field of composite material functionalization, and relates to a method for non-interference monitoring impact threat of a composite material part structure. Background technique [0002] As far as the performance of laminated composites (composite laminates) is concerned, impact damage resistance and impact damage tolerance are currently known to be the most important structural performance indicators. When a small-sized near-rigid foreign body is impacted at a low speed, delamination damage usually occurs inside the composite material, which seriously reduces its mechanical properties and structural safety and reliability. For this kind of delamination damage, the existing method must be found through complex non-destructive monitoring. This method has poor flexibility and convenience for composite parts that have served in the field. Therefore, it is necessary to improve the impact damage resistance of composite...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B29C70/02G01M7/08
Inventor 益小苏张明刘刚安学锋张连旺
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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