CN105153950A - Repairing structure with composite repairing piece and method for forming repairing structure - Google Patents
Repairing structure with composite repairing piece and method for forming repairing structure Download PDFInfo
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- CN105153950A CN105153950A CN201510620302.3A CN201510620302A CN105153950A CN 105153950 A CN105153950 A CN 105153950A CN 201510620302 A CN201510620302 A CN 201510620302A CN 105153950 A CN105153950 A CN 105153950A
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- composite
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Abstract
The invention discloses a repairing structure with a composite repairing piece and a method for forming the repairing structure and belongs to the technology of composite repairing. The repairing structure is composed of a repaired damaged composite structure, the composite repairing piece, glue between the composite repairing piece and the composite structure, and a sewing thread steeped with a cementing compound. Firstly, small holes penetrating through the repairing piece, the damaged composite structure and a glue layer between the repairing piece and the damaged composite structure are machined in a repairing piece repairing part; secondly, the sewing thread steeped with the cementing compound sequentially penetrates into the small holes; lastly, curing is carried out at the regulated temperature and pressure, so that the sewing thread are bonded to the repairing piece around the sewing thread and the damaged composite structure together, and thus the repairing structure with the repairing piece is formed. By means of the repairing structure formed through the method, the influence on the performance in a composite laminated plate face is small, the environmental sensitivity is reduced, and the weight of the structure is slightly increased; in addition, the bonding effect between the composite repairing piece and the repaired structure can be improved, so that the mechanical property and the reliability of the repairing structure with the composite repairing piece are improved, and the use risk of the repaired composite structure is lowered.
Description
Technical field
The invention belongs to repairing composite material field, be specifically related to a kind ofly between sticking patch and impaired composite structure, penetrate the sticking patch preparing structure of suture and form the method for described preparing structure, the preparing structure that using said method is made has higher reliability and supporting capacity.
Background technology
The anti-fatigue performance that resin base fiber reinforcement advanced composite material has specific tenacity and specific rigidity is high, designability is strong, good, erosion resistance is good and be convenient to the advantages such as global formation, be widely used in the military fields such as aircraft, guided missile, rocket and man-made satellite, and the civil area such as racing car, boats and ships, bullet train, bridge and wind-power blade.But due to its manufacturing process and handling characteristics thereof, matrix material very easily produces defect and damage.These defects and damage comprise three classes substantially, one class is the surface damage comprising surface tear, cut, slight crack, shallow-layer breach and indenture isotype, one class is the delamination damage between the different individual layer of matrix material, also have a class be because of fibre breakage and damaged and produces crack, tear and damage with the laying such as breach.The recovery of the structural strength after repairing and rigidity should be made high as far as possible to the reparation of these damages, make the increase of structural weight little as far as possible, also will recover the using function of primary structure.
Impaired matrix material is reapposed and repairs in autoclave, time and money cost is higher.And new damage may be caused again due to repair procedures by the part repaired, as due to overheated and at certain temperature long time and cause layering or unsticking.Therefore, the damage scene that relies on for composite structure places under repair more.At the scene in repair method, resin injection method and filler are filled legal system and are used for less edge delamination, unsticking and the surface crater equivalent damage lower to structural mechanic of complex material performance impact.For major injuries such as the layering of matrix material big area, fibre breakages, machinery or bonded process in Practical Project, is usually used to place under repair.Wherein, repair of machine method is easier, and processing performance is more stable, not by the impact of construction environment.But application the method is repaired, and can produce serious stress concentration at nail place, and have the etching problem of fastening piece, the life-span is relatively short.Therefore, repair of machine method is used for meeting emergency situation usually used as temporary reqair.Bonding Repair comprises and subsidizes and mend by replacing a damaged part two kinds of repair methods.The structure that application Bonding Repair method is repaired, the life-span is longer, uses usually used as permanent repair.But this repairing structure transmits sticking patch by glue-line and by the load of repairing between composite structure, therefore, reliability is low, to environment sensitive, glue-line damage not easily detects.In addition, the end of subsidizing the outer embedding sticking patch subsidized sheet and mend REPSH repair shop use by replacing a damaged part that REPSH repair shop uses all requires smaller key groove (point is slightly than being generally 15:1), concentrates to reduce end stress.Less key groove causes patch size comparatively large (as diameter being the damage of 20 millimeters, the diameter of sticking patch is approximately 60 ~ 80 millimeters), causes subsidizing repairing and increases weight more, mending by replacing a damaged part to repair needs to remove a large amount of non-attacking material, and be difficult to return to original intensity, improve structure risk.
Therefore, need to develop reliable composite panels and repair structure and method, reduce patch size, the effect that raising is repaired, thus recover to a greater degree or improve the mechanical property of repairing rear composite structure.
Summary of the invention
The object of the invention is to, overcome current adhesive bonding of composites repair method reliability low, to environment sensitive and the shortcoming such as more that increases weight, and a kind of advanced composite material structure patch structure and novel method are provided, reduce patch size and structural weight, and improve repairing composite material reliability of structure and supporting capacity.
The present invention solves the problems of the technologies described above adopted technical scheme:
A kind of composite panels preparing structure, is characterized in that:
A, preparing structure forms by by the suture of repairing damaged composite structure, composite panels, glue between composite panels and composite structure and impregnated resin stick;
B, suture through composite panels and composite structure, and is bonded together by the tackiness agent on suture and composite panels and composite structure.
Further, the diameter of described suture is 0.5 ~ 1.5 millimeter, while proof strength, less on the in-plane mechanical properties impact of passed composite panels and composite structure.
Further, the material of described suture comprises the glass fiber bundle of impregnated resin stick, carbon fiber bundle, boron fibre bundle and aramid fiber bundle etc.
Further, the size of described sticking patch is less, and point is slightly smaller, is 1:1 to 8:1, thus reduces the size of sticking patch and weight and repairing work load.
Further, comprising of described sticking patch outer subsidized sheet and embeds sticking patch, and corresponding repairing type is respectively to subsidize and repairs and mend repairing by replacing a damaged part.
Further, described suture bobbin is to consistent with matrix material normal direction or vertical with the bonding surface between sticking patch with repaired structure.
For realizing the object of the invention, adopting a kind of method forming described preparing structure, comprising the steps:
(1) damage field and the degree of composite structure is determined;
(2) damage zone process, comprises surface finish, removes damaged material and drying etc.;
(3) according to the result of damage field and degree and damage zone, the suture of composite panels, glue and impregnated resin stick is prepared;
(4) sticking patch is laid on injury region, and places one deck glue between sticking patch and impaired composite structure;
(5) repair at sticking patch the aperture that position processing runs through sticking patch and impaired composite structure and glue-line therebetween;
(6) suture being soaked with tackiness agent is penetrated each aperture successively;
(7) at specified temperature and cure under pressure, suture and the sticking patch around it and impaired composite structure are bonded together;
(8) temperature and pressure application devices is removed.
Further, in described step (four), the laying method of sticking patch is determined by the initial configuration of sticking patch:
If patching material is prepreg, then prepreg is laid in patch area according to the direction specified and the number of plies;
If patching material is pre-hardening thickness plywood, the direction of pre-hardening thickness plywood according to regulation is located and be installed on patch area;
As fabric or one-way tape that patching material is non-impregnated resin stick, then adopt the method for wet paving, be aided with resin or tackiness agent, fabric or one-way tape are laid in patch area according to the direction specified and the number of plies.
Further, aperture makes and uses high energy and the less laser apparatus of heat-dissipating or microbit in described step (five), ensure drilling position matrix material can not or less ablated.
Further, larger than suture 0.1 ~ 0.3 millimeter of the diameter of aperture in described step (five), what be convenient to suture on the one hand penetrates aperture, can ensure the bonding quality between all materials of suture and hole on the other hand.
Further, the solidification of described step (seven) tackiness agent, according to adhesive solidification requirement used, in conjunction with heating installations such as vacuum bag and electric blanket, infrared lamp, heat gun and temperature controlling instrumentss, under the vacuum pressures patch area is temporally applied to the temperature specified, make the surperficial tackiness agent of uncured sticking patch, the glue-line between sticking patch and repaired structure, thin rod complete solidification simultaneously.
Beneficial effect of the present invention is: propose a kind of advanced composite material sticking patch preparing structure and form the method for described preparing structure, adopt preparing structure made by present method, less to performance impact in composite laminated plate face, environmental sensitivity is reduced, less to structure weightening finish, and the keying action that can improve between composite panels and repaired structure, thus the mechanical property and the reliability that improve that composite panels repairs structure, reduce the application risk of composite structure after repairing.
Accompanying drawing explanation
Fig. 1 patched by FRP repairs structural section figure;
Fig. 2 patched by FRP repairs STRUCTURE DECOMPOSITION figure;
Fig. 3 matrix material is mended by replacing a damaged part and is repaired structural section figure;
Fig. 4 matrix material is mended by replacing a damaged part and is repaired STRUCTURE DECOMPOSITION figure;
In figure, 11 are repaired composite laminated plate, subsidize sheet outside 12,13 is glue, and 14 is sutures, and 21 are repaired composite laminated plate, subsidize sheet outside 22,33 is glue, and 34 is sutures, 31 are repaired composite laminated plate, and 32 embed sticking patch, and 33 is glue, 34 is sutures, and 41 are repaired composite laminated plate, and 42 embed sticking patch, 43 is glue, and 44 is sutures.
Embodiment
Below in conjunction with drawings and embodiments, this aspect is described further.
Embodiment 1
Application Procuring sheet and proposed method, be that the crack and damage of the epoxy resin base carbon fiber reinforced composite structure of 4 millimeters subsidizes repairing to thickness, step is as follows:
(1) damage field of composite structure and degree is determined to be length is the crack and damage of 4 millimeters;
(2) tackiness agent in residual repairing district and sealing agent is first removed, then drilling process is applied, remove the material within the scope of crack and damage circumscribed circle, after finally using vacuum cleaner clean repair district, district is repaired respectively by No. 180 and No. 360 sand paperings, repair district by solvent cleaned, and carry out local heating drying with heat gun;
(3) according to the result of damage field and degree and damage zone, prepare matrix material Procuring sticking patch (diameter is 16 millimeters, thickness is 2 millimeters, point slightly than be 2:1), TESA8432 hot melt adhesive film (diameter be 16 millimeters, thickness be 0.2 millimeter) and flood the carbon fiber suture (length be 500 millimeters, diameter be 0.7 millimeter) of hot setting adhesive J-47 tackiness agent;
(4) glued membrane is laid in injury region, then places Procuring sticking patch according to the direction of regulation thereon, and make center and the damage zone center superposition of glued membrane and sticking patch;
(5) using miniature inserted drill repairs at sticking patch the aperture (hole diameter is 0.8 millimeter) that position processing runs through sticking patch and impaired composite structure and glue-line therebetween;
(6) carbon fiber suture being soaked with SY-14 tackiness agent is penetrated each aperture successively, after tension suture, cut off redundance;
(7), under application vacuum bag makes patch area be in vacuum pressure, application electric blanket carries out local heating to patch area and (keeps temperature to be 130 ± 5
oc, the time is 3 hours), make the J-47 adhesive solidification on TESA8432 glued membrane and suture, thus suture and the sticking patch around it and impaired composite structure are bonded together;
(8) vacuum bag and electric blanket is removed.
Adopt this repairing Enhancement Method, to process hole diameter less, less to performance impact in the face of composite laminated plate and sticking patch, suture not only plays crack arrest effect, and transmit the load of sticking patch and impaired composite structure together with glue-line, thus improve the reliability and mechanical property of repairing rear composite laminated plate.
Embodiment 2
Application prepreg and proposed method, be that the delamination damage of the inside of the epoxy resin base carbon fiber reinforced composite structure of 6 millimeters mends repairing by replacing a damaged part to thickness, step is as follows:
(1) determine that there is delamination damage at the inner 3 mm depth places of composite structure, the circumscribed circle of delamination damage is 8 millimeters;
(2) material of portable pneumatic copying milling excision damage field is used, the excision district degree of depth 3 millimeters, base diameter is 8 millimeters, the gradient 3:1 at edge, then applies sand papering, obtains smooth inclined-plane, after finally using vacuum cleaner clean repair district, repair district by No. 180 and No. 360 sand paperings respectively, repair district by solvent cleaned, and carry out local heating drying with heat gun;
(3) according to the result of damage field and degree and damage zone, prepare the carbon fiber suture (length be 1000 millimeters, diameter be 1.2 millimeters) of the material prepreg sheet (minimum prepreg diameter is 8 millimeters, maximum diameter 32 millimeters) of different size, 3M615 hot melt adhesive film (diameter be 40 millimeters, thickness be 0.2 millimeter) and dipping intermediate temperature setting adhesive SY-14 tackiness agent;
(4) glued membrane is laid in bottom excision district, then thereon according to direction and order (bottom the prepreg close excision district that diameter is less, maximum covers outside damage zone) the successively lay prepreg of regulation;
(5) apply TruMicro5050 laser apparatus and repair at sticking patch the aperture (hole diameter is 1.5 millimeters) that position processing runs through sticking patch and impaired composite structure and glue-line therebetween;
(6) carbon fiber suture being soaked with SY-14 tackiness agent is penetrated each aperture successively, after tension suture, cut off redundance;
(7), under application vacuum bag makes patch area be in vacuum pressure, application electric blanket carries out local heating to patch area and (keeps temperature to be 175 ± 5
oc, the time is 5 hours), make the SY-14 adhesive solidification on 3M615 glued membrane and suture, thus suture and the sticking patch around it and impaired composite structure are bonded together;
(8) vacuum bag and electric blanket is removed.
Adopt this repairing Enhancement Method, to process hole diameter less, less to performance impact in the face of composite laminated plate and sticking patch, suture not only plays crack arrest effect, and transmit the load of sticking patch and impaired composite structure together with glue-line, thus improve the reliability and mechanical property of repairing rear composite laminated plate.
Claims (7)
1. a composite panels preparing structure, is characterized in that:
A, preparing structure forms by by the suture of repairing damaged composite structure, composite panels, glue between composite panels and composite structure and impregnated resin stick;
B, suture through composite panels and composite structure, and is bonded together by the tackiness agent on suture and composite panels and composite structure.
2. structure according to claim 1, is characterized in that: the diameter of described suture is 0.5 ~ 1.5 millimeter.
3. structure according to claim 1, it is characterized in that: the size of described sticking patch is less, point is slightly smaller.
4. according to claim 3 point slightly than, it is characterized in that: its value is 1:1 to 8:1.
5. form a method for sticking patch preparing structure, it is characterized in that, comprise the steps:
(1) damage field and the degree of composite structure is determined;
(2) damage zone process, comprises surface finish, removes damaged material and drying etc.;
(3) according to the result of damage field and degree and damage zone, the suture of composite panels, glue and impregnated resin stick is prepared;
(4) sticking patch is laid on injury region, and places one deck glue between sticking patch and impaired composite structure;
(5) repair at sticking patch the aperture that position processing runs through sticking patch and impaired composite structure and glue-line therebetween;
(6) suture being soaked with tackiness agent is penetrated each aperture successively;
(7) at specified temperature and cure under pressure, suture and the sticking patch around it and impaired composite structure are bonded together;
(8) temperature and pressure application devices is removed.
6. method according to claim 5, is characterized in that: in described step (five), aperture makes and uses high energy and the less laser apparatus of heat-dissipating or microbit.
7. method according to claim 5, is characterized in that: larger than suture 0.1 ~ 0.3 millimeter of the diameter of aperture in described step (five).
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Cited By (8)
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| CN106226393A (en) * | 2016-07-05 | 2016-12-14 | 国营芜湖机械厂 | A kind of laminate composite structural stratification damage rehabilitation method |
| CN106891555A (en) * | 2017-03-03 | 2017-06-27 | 马琳 | Using the method for ultrasonic heat in-situ repair thermoplastic composite defect |
| CN108437497A (en) * | 2018-03-19 | 2018-08-24 | 中国南方航空股份有限公司 | A kind of engine is counter to push away grid typical damage renovation technique |
| CN108791951A (en) * | 2018-03-19 | 2018-11-13 | 中国南方航空股份有限公司 | A method of the anti-push part of aircraft is repaired using ablation |
| CN110087868A (en) * | 2016-12-20 | 2019-08-02 | 罗尔公司 | Acoustic properties is able to the machine vision acoustic panels reparation retained |
| CN111122319A (en) * | 2019-12-19 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Composite material cementing repair structure strength evaluation method |
| CN112507454A (en) * | 2020-12-04 | 2021-03-16 | 中国航空工业集团公司成都飞机设计研究所 | Fiber layering and layer losing method for reinforcing large-area metal structure composite material |
| CN112961459A (en) * | 2021-02-02 | 2021-06-15 | 中车青岛四方机车车辆股份有限公司 | Repairing material and repairing method |
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Cited By (12)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106226393A (en) * | 2016-07-05 | 2016-12-14 | 国营芜湖机械厂 | A kind of laminate composite structural stratification damage rehabilitation method |
| CN106226393B (en) * | 2016-07-05 | 2020-01-31 | 国营芜湖机械厂 | layered damage repairing method for laminated composite material structure |
| CN110087868A (en) * | 2016-12-20 | 2019-08-02 | 罗尔公司 | Acoustic properties is able to the machine vision acoustic panels reparation retained |
| US11104086B2 (en) | 2016-12-20 | 2021-08-31 | Rohr, Inc | Machine vision acoustic panel repair with retention of acoustic properties |
| CN110087868B (en) * | 2016-12-20 | 2021-10-22 | 罗尔公司 | Machine vision acoustic panel repair with acoustic properties preserved |
| CN106891555A (en) * | 2017-03-03 | 2017-06-27 | 马琳 | Using the method for ultrasonic heat in-situ repair thermoplastic composite defect |
| CN108437497A (en) * | 2018-03-19 | 2018-08-24 | 中国南方航空股份有限公司 | A kind of engine is counter to push away grid typical damage renovation technique |
| CN108791951A (en) * | 2018-03-19 | 2018-11-13 | 中国南方航空股份有限公司 | A method of the anti-push part of aircraft is repaired using ablation |
| CN108791951B (en) * | 2018-03-19 | 2022-03-08 | 中国南方航空股份有限公司 | Method for maintaining airplane reverse thrust component by ablation method |
| CN111122319A (en) * | 2019-12-19 | 2020-05-08 | 中国航空工业集团公司西安飞机设计研究所 | Composite material cementing repair structure strength evaluation method |
| CN112507454A (en) * | 2020-12-04 | 2021-03-16 | 中国航空工业集团公司成都飞机设计研究所 | Fiber layering and layer losing method for reinforcing large-area metal structure composite material |
| CN112961459A (en) * | 2021-02-02 | 2021-06-15 | 中车青岛四方机车车辆股份有限公司 | Repairing material and repairing method |
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