CN205601282U - Many functional composite material of selfreparing structure - Google Patents
Many functional composite material of selfreparing structure Download PDFInfo
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- CN205601282U CN205601282U CN201620294314.1U CN201620294314U CN205601282U CN 205601282 U CN205601282 U CN 205601282U CN 201620294314 U CN201620294314 U CN 201620294314U CN 205601282 U CN205601282 U CN 205601282U
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Abstract
The utility model relates to a combined material discloses a many functional composite material of selfreparing structure very much. This many functional composite material of selfreparing structure, including the combined material main part, its characterized in that: the upper surface subsides of combined material main part are covered with three -dimensional metallic network, and the lower surface subsides are covered with plane metallic network, and the subsides of three -dimensional metallic network upper surface are covered with combined material upper portion apron, and plane metallic network lower surface subsides are covered with combined material lower part apron. The utility model discloses increase the intensity and the modulus of combined material thickness direction, increased combined material's a layer fracture toughness and the ability that anti layering produced and expanded, increased combined material's anti impact damage ability and antifatigue layering extended capability.
Description
(1) technical field
This utility model relates to a kind of composite, particularly to a kind of selfreparing multifunctional composite structure.
(2) background technology
Fiber-reinforced resin matrix compound material is excellent owing to specific stiffness, specific strength height, good corrosion resistance, performance can design etc.
Point, becomes the high-strength light structural material of a new generation, is widely used in the field such as Aeronautics and Astronautics, automobile.But be limited to fold
The feature of Rotating fields, composite laminated plate because of during being on active service normal load, exotic impact etc. and easily at laminate
Between crack, also referred to as delamination damage.
Delamination damage is the modal type of impairment of laminate structures composite, owing to it results from inside laminate, difficult
To be facilitated and to be reliably detected.Delamination damage to composite detects the visual and ultrasonic two ways of main employing at present.
Visual detection causes the produced surface crater of exotic impact of layering by discovery, identifies delamination damage and position thereof.
But, by pit size, finish coatings state, light, detecting distance and comfort level, and the anthropic factor etc. of tester
The impact of many-sided condition, its detection reliability is limited.And although ultrasound detection reliability is higher, but due to inefficient, only
Within the limited time, specific region can be carried out damage check.
Some real-time architecture health monitoring technique is had been developed at present, by modes such as piezoelectric transducer or implantation optical fiber
Realize real-time monitoring of structures faulted condition, substantially increase the reliability of structure detection, promptness.But this technology is owing to bringing
Extra weight but without otherwise income, is not widely used in engineering structure.
Containing the repair method of delamination damage composite structure, use modes such as mending by replacing a damaged part and subsidize traditionally.First will damage
The material hindering region is removed regularly, by glueing joint or sticking patch being connected to by the way of mechanical connection damage field, to recover knot
The bearing capacity of structure.But this conventional art is the most expensive, and the most time-consuming.
The impact brought structure due to above-mentioned delamination damage, the design of current Test of Laminate Composites structure all have employed
Higher margin of safety ensures the safety of structure.Most typical example is to be applied to the design " damage of civil aircraft main structure
Require without extension ", i.e. the composite structure containing delamination damage is in certain active time, must not carry owing to undertaking reciprocating fatigue
Lotus and produce harmful extension.In order to reach this safety requirements, have employed relatively low bearing stress level when structure designs
Deng conservative design, thus sacrifice construction weight and efficiency.
(3) summary of the invention
This utility model is in order to make up the deficiencies in the prior art, it is provided that a kind of performance enhancement, structural health are monitored in real time
Selfreparing multifunctional composite structure.
This utility model is achieved by the following technical solution:
A kind of selfreparing multifunctional composite structure, including composite body, it is characterised in that: described composite
The upper surface of main body has sticked 3-dimensional metal network, and lower surface has sticked planar metal network, and 3-dimensional metal network upper surface pastes
Being covered with composite top cover plate, planar metal network lower surface has sticked composite material lower cover plate.
Composite body of the present utility model is manufactured by carbon fiber or glass fiber resin based composites, it is possible to use
Other fibre resin based composites, its preparation technology can be prepreg autoclave technique, it is also possible to be dry fibers resin note
Molded or other liquid molding process, its main body acting as undertaking structural loads.
On the one hand this utility model improves the interlaminar strength of Test of Laminate Composites structure and resists the ability that layering produces,
On the other hand provide a kind of being rapidly performed by after hierarchical crack produces to repair, and the method recovering structural-load-carrying capacity；?
On the one hand provide a kind of means that can carry out monitoring structural health conditions in real time simultaneously.
More excellent technical scheme of the present utility model is:
The top of described 3-dimensional metal network is the wire netting that plane interweaves, and wire netting Vertical Square extends upward with it even
The tinsel connect, for three-dimensional net structure；It act as: on the one hand forms the tinsel that through-thickness strengthens, strengthens structure
The performance of thickness direction；On the other hand make tinsel be interconnected to form network, provide circuit for heating coating and health monitoring.
The tinsel of described 3-dimensional metal network runs through composite body and is connected with the planar metal network of bottom, its
Effect is after 3-dimensional metal network is implanted in composite body, from the another one direction of composite body with three-dimensional
The thickness direction tinsel of metalolic network connects, and is formed by the power circuit of 3-dimensional metal network to planar metal network.
Metalolic network surface, described 3-dimensional metal network peace face all scribbles thermoplastic resin coating, and coating is after being heated
Flowable go out to neighbouring connected layering and crackle, play repair.
Described composite body, composite top cover plate and composite material lower cover plate are carbon fiber or glass fibers
Dimension polymer matrix composites, it is possible to using other polymer matrix composites of similar performance, the effect of top and the bottom cover plate has been close
Envelope effect, prevents the thermoplastic resin being heated during structure repair from flowing out.
Several energising terminals it are provided with, it is achieved that the input of electric current on the metalolic network of described 3-dimensional metal network peace face
And output.
This utility model adds intensity and the modulus in thickness of composite material direction, adds the interlayer faults of composite
Toughness and anti-layering produce and the ability of extension, add shock resistance lesion capability and the resisting fatigue delamination energy of composite
Power, can repair the layering in composite and crackle, to recover the bearing capacity of structure, it is possible to achieve to composite
Delamination damage region and the detection of size, add electrical conductivity and the thermal conductivity of composite.
(4) accompanying drawing explanation
Below in conjunction with the accompanying drawings this utility model is further described.
Fig. 1 is structural representation of the present utility model；
Fig. 2 is the view of 3-dimensional metal network composite implant material main body；
Fig. 3 is layering generation in the composite but does not causes the situation schematic diagram of wire breakage；
Fig. 4 be described in Fig. 3 in the case of carry out the mobility status schematic diagram of thermoplastic resin during structure repair；
Fig. 5 is that layering produces the situation schematic diagram simultaneously causing wire breakage in the composite；
Fig. 6 be described in Fig. 5 in the case of carry out the mobility status schematic diagram of thermoplastic resin during structure repair.
In figure, 1 composite body, 2 3-dimensional metal networks, 3 planar metal networks, 4 composite top cover plates, 5 is multiple
Condensation material bottom cover plate, 11 energising terminals, 21 wire nettings, 22 tinsels, 101 hierarchical cracks, 102 layerings cause wire breakage
Part, 201 metal twines, 202 thermoplastic resin coating, 203 along the flowing coating of hierarchical crack.
(5) detailed description of the invention
Accompanying drawing is a kind of specific embodiment of the present utility model.This embodiment includes composite body 1, described composite wood
The upper surface of material main body 1 has sticked 3-dimensional metal network 2, and lower surface has sticked planar metal network 3, on 3-dimensional metal network 2
Surface has sticked composite top cover plate 4, and planar metal network 3 lower surface has sticked composite material lower cover plate 5；Described three
The top of dimension metalolic network 2 is the wire netting 21 that plane interweaves, and wire netting 21 Vertical Square extends upward connected metal
Silk 22；The tinsel 22 of described 3-dimensional metal network 2 runs through composite body 1 and is connected with the planar metal network 3 of bottom；
Described 3-dimensional metal network 2 and plane metalolic network 3 surface all scribble thermoplastic resin coating 202；Described composite body
1, composite top cover plate 4 and composite material lower cover plate 5 are carbon fiber or glass fiber resin based composites；Described
Several energising terminals 11 it are provided with on 3-dimensional metal network 2 and plane metalolic network 3.
Following forming technology is used to prepare the multifunctional composite in the present invention:
Use tradition laying mode to carry out the laying of composite body 1, prepreg one-way tape, fabric can be used, it is possible to
To use dry silk one-way tape or fabric.As used prepreg, it is pre-that 3-dimensional metal network 2 is implanted to after laying by available pressure sintering
In formed body；As used dry silk material, can use and be pressed directly into the preform after 3-dimensional metal network 2 is implanted to laying by method
In.Thickness according to composite body 1 designs the height of tinsel 22 in 3-dimensional metal network 2, can be from after being allowed to implant
Certain length is stretched out in bottom, by local hot melt or mechanical means, removes the thermoplastic resin coating 202 of extension.Will
After planar metal network 3 is placed into bottom, the extension of tinsel 22 is bent, is pressed into, is allowed to and planar metal net
Network 3 connects formation power circuit.After composite top cover plate 4 and composite material lower cover plate 5 laying laying, plant on demand
Enter a number of energising terminal 11.
Depending on curing process is according to the material of composite body, the solidification of autoclave technique, solidification are used for prepreg
Temperature should be less than the melt temperature of the thermoplastic resin coating 202 in 3-dimensional metal network 2.If solidification temperature is higher than thermoplasticity
Resin cladding 202 melt temperature, then should cured in stages, first stage solidification temperature be less than coating melt temperature, second-order
Section applies the solidification temperature of requirement again.For dry silk material, resin injection molding or other liquid can be directly used to shape solidification
Technique.
When by finding to occur the hierarchical crack as shown in accompanying drawing 3 such as detection meanss such as ultrasonic scannings, at energising terminal
Switch on power between 11 so that metalolic network produce required for electric current and generate heat, resin cladding melted by heating flow, such as accompanying drawing 4
Shown in, it is filled with hierarchical crack it is achieved thereby that to structure repair.
When realizing monitoring structural health conditions function, apply a little voltage between energising terminal 11 and measure between them
Resistance.When there is the hierarchical crack shown in accompanying drawing 5, the resistance between energising terminal 11 is due to the gold near fracture position
Belong to silk to be cut off and increased, compare with the measuring resistance demarcated, it can be determined that go out region and size that layering produces.This
Time carry out molten resin coating by the external heat source such as electric blanket or infrared heating and be caused to flow, as shown in Figure 6, it is achieved to knot
The reparation of structure.
Claims (6)
1. a selfreparing multifunctional composite structure, including composite body (1), it is characterised in that: described composite wood
The upper surface of material main body (1) has sticked 3-dimensional metal network (2), and lower surface has sticked planar metal network (3), dimensional metal mesh
Network (2) upper surface has sticked composite top cover plate (4), and planar metal network (3) lower surface has sticked composite material lower
Cover plate (5).
Selfreparing multifunctional composite structure the most according to claim 1, it is characterised in that: described 3-dimensional metal network
(2) top is the wire netting (21) that plane interweaves, and wire netting (21) Vertical Square extends upward connected tinsel
(22).
Selfreparing multifunctional composite structure the most according to claim 2, it is characterised in that: described 3-dimensional metal network
(2) tinsel (22) runs through composite body (1) and is connected with the planar metal network (3) of bottom.
Selfreparing multifunctional composite structure the most according to claim 1, it is characterised in that: described 3-dimensional metal network
And plane metalolic network (3) surface all scribbles thermoplastic resin coating (202) (2).
Selfreparing multifunctional composite structure the most according to claim 1, it is characterised in that: described composite body
(1), composite top cover plate (4) and composite material lower cover plate (5) are carbon fiber or glass fiber resin base composite wood
Material.
Selfreparing multifunctional composite structure the most according to claim 1, it is characterised in that: described 3-dimensional metal network
(2) several energisings terminal (11) and it are provided with on plane metalolic network (3).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620294314.1U CN205601282U (en) | 2016-04-11 | 2016-04-11 | Many functional composite material of selfreparing structure |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620294314.1U CN205601282U (en) | 2016-04-11 | 2016-04-11 | Many functional composite material of selfreparing structure |
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| CN205601282U true CN205601282U (en) | 2016-09-28 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105965996A (en) * | 2016-04-11 | 2016-09-28 | 山东利普索航空科技有限公司 | Self-repairing multifunctional composite material structure |
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2016
- 2016-04-11 CN CN201620294314.1U patent/CN205601282U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105965996A (en) * | 2016-04-11 | 2016-09-28 | 山东利普索航空科技有限公司 | Self-repairing multifunctional composite material structure |
| CN105965996B (en) * | 2016-04-11 | 2018-02-13 | 山东利普索航空科技有限公司 | A kind of selfreparing multifunctional composite structure |
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