CN105881931A - Complementation method for hole of large sandwich-structure composite cabin - Google Patents
Complementation method for hole of large sandwich-structure composite cabin Download PDFInfo
- Publication number
- CN105881931A CN105881931A CN201610214057.0A CN201610214057A CN105881931A CN 105881931 A CN105881931 A CN 105881931A CN 201610214057 A CN201610214057 A CN 201610214057A CN 105881931 A CN105881931 A CN 105881931A
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- China
- Prior art keywords
- aperture
- composite material
- embedded part
- structure composite
- sandwich structure
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
- B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/36—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and impregnating by casting, e.g. vacuum casting
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
Abstract
The invention relates to a complementation method for a hole of a large sandwich-structure composite cabin. The method comprises the following steps that the periphery of the hole, needing to be complemented, of the large sandwich-structure composite cabin is cut to form a cut opening with a slope; a prefabricated sandwich embedded part with the shape matched with that of the hole is put into the hole, wherein chamfers are arranged at the two ends of the sandwich embedded part, and two prefabricated grooves each of a slope structure are formed by the sandwich embedded part and the cut opening in the periphery of the hole; prefabricated parts are laid in the two prefabricated grooves layer by layer; resin is injected onto the two prefabricated parts through vacuum assistance; and after the injected resin is cured, the complemented surface is polished, and the planeness of the complemented surface and the planeness of an original large composite cabin wall keep consistent. According to the complementation method, cost is reduced, the comprehensive utilization efficiency of the composite cabin is increased, and process operation is easy; and the phenomenon that scrapping happens due to the fact that a hole cannot be complemented in the refitting process of a traditional large sandwich-structure square cabin is eliminated.
Description
Technical field
The present invention relates to the complementing method in a kind of nacelle aperture, be specifically related to a kind of large-scale sandwich multiple
The complementing method in condensation material nacelle aperture.
Background technology
Along with the fast development of composite industry, the large-scale nacelle of composite in use can not
There is the phenomenon of repacking in the meeting avoided, for the hole occurred in large-scale interlayer composite material shelter retrofit process
Mouth completion problem becomes one of difficult problem urgently to be resolved hurrily.
Summary of the invention
The technical problem to be solved is to provide a kind of simple to operate, cost-effective large-scale interlayer
The complementing method in structural composite material nacelle aperture.
The technical scheme is that a kind of large-scale sandwich structure composite material
The complementing method in nacelle aperture, comprises the following steps,
Step one, the surrounding in the large-scale sandwich structure composite material nacelle aperture needing completion is cut
Cut, formed and carry sloping otch, and the aperture after cutting is cleaned dried；
Step 2, puts making that match with orifice shapes and two ends in advance with the interlayer embedded part of chamfering
Put in aperture, and the chamfering at described interlayer embedded part two ends is corresponding with the otch of aperture surrounding, described folder
The chamfering at layer embedded part two ends forms the pregroove marks of two shelving structures with the otch of aperture surrounding；
Step 3, the most successively lays prefabricated component in two pregroove marks；
Step 4, utilizes vacuum aided to infuse resin on two prefabricated components, makes resin complete wetting two
Prefabricated component and interlayer embedded part；
Step 5, after the resin solidification injected, the surface of polishing completion so that putting down of the surface of completion
Face degree keeps consistent with the flatness of former large-scale composite material nacelle wall.
The invention has the beneficial effects as follows: the benefit in a kind of large-scale sandwich structure composite material nacelle aperture of the present invention
Full method, in the nacelle treating completion aperture, uses the vacuum assisted process optimized, disposably by big chi
Very little and have the aperture of special formed shelter to carry out completion, not only save cost, the composite of increase
The comprehensive utilization ratio of nacelle, technological operation is simple, and compensate for traditional large-scale sandwich shelter and change
The phenomenon scrapped owing to can not carry out aperture completion in process of assembling, imparts large-scale sandwich and is combined
The use that material shelter is new.
On the basis of technique scheme, the present invention can also do following improvement.
Further, the slope length range of described otch is 50mm～70mm, and slope depth bounds is
5mm～7mm.
Further, the chamfering length range of described interlayer embedded part is 50mm～70mm, and depth bounds is
5mm～7mm.
Further, the chamfering length of described interlayer embedded part is identical with the slope length of described otch, described folder
The depth of chamfering of layer embedded part is identical with the slope degree of depth of described otch.
Further, in step 4, utilize method that vacuum aided infuses resin on prefabricated component specifically,
First dismoulding system, flow guide system, injection system and close is the most jointly laid on the surface of two prefabricated components
Envelope system；Then utilize vacuum extractor to sealing system evacuation, under conditions of vacuum, utilize injecting glue
System resin by injection, and it is complete to make the resin of injection pass through dismoulding system under the guide functions of flow guide system
Infiltrate two prefabricated components and interlayer embedded part.
Further, in step 5, carrying out the demoulding after the resin solidification injected, the method for the demoulding is concrete
For sloughing sealing system, injection system, flow guide system and the dismoulding system on prefabricated component successively.
Further, described dismoulding system is release cloth；Described flow guide system includes flow-guiding screen and mozzle,
Described mozzle is positioned at the top of described flow-guiding screen；Described sealing system includes vacuum bag and sealant tape,
Described vacuum bag is bonded in large-scale sandwich structure composite material nacelle by sealant tape, and by laying
Two prefabricated components are sealed in vacuum bag.
Further, the vacuum≤-0.095Mpa of described sealing system, in pressurize one Preset Time,
Pressure≤-the 0.075Mpa of sealing system.
Further, described interlayer embedded part is PVC foamed materials.
Further, described prefabricated component includes reinforcement and eyelid covering, reinforcement layer from narrow to wide described in multilamellar
Being layered in pregroove marks, eyelid covering described in multilamellar is laid on reinforcement and described pregroove marks is filled full.
Accompanying drawing explanation
Fig. 1 is the flow process of the complementing method in a kind of large-scale sandwich structure composite material nacelle aperture of the present invention
Figure；
Fig. 2 is the structural representation of the completion in a kind of large-scale sandwich structure composite material nacelle aperture of the present invention
Figure.
In accompanying drawing, the list of parts representated by each label is as follows:
1, large-scale sandwich structure composite material shelter, 2, interlayer embedded part, 3, prefabricated component, 4, the demoulding
System, 5, flow guide system, 6, injection system, 7, sealing system.
Detailed description of the invention
Being described principle and the feature of the present invention below in conjunction with accompanying drawing, example is served only for explaining this
Invention, is not intended to limit the scope of the present invention.
As it is shown in figure 1, the complementing method in a kind of large-scale sandwich structure composite material nacelle aperture, including with
Lower step,
Step one, the surrounding in the large-scale sandwich structure composite material nacelle aperture needing completion is cut
Cut, formed and carry sloping otch, and the aperture after cutting is cleaned dried.Described otch
Slope length range be 50mm～70mm, slope depth bounds is 5mm～7mm.
Step 2, puts making that match with orifice shapes and two ends in advance with the interlayer embedded part of chamfering
Put in aperture, and the chamfering at described interlayer embedded part two ends is corresponding with the otch of aperture surrounding, described folder
The chamfering at layer embedded part two ends forms the pregroove marks of two shelving structures with the otch of aperture surrounding.Described interlayer
Embedded part is PVC foamed materials.The chamfering length range of described interlayer embedded part is 50mm～70mm, degree of depth model
Enclose for 5mm～7mm.The chamfering length of described interlayer embedded part is identical with the slope length of described otch, described
The depth of chamfering of interlayer embedded part is identical with the slope degree of depth of described otch.
Step 3, the most successively lays prefabricated component in two pregroove marks.Described prefabricated component include reinforcement and
Eyelid covering, reinforcement layer from narrow to wide described in multilamellar is layered in pregroove marks, and eyelid covering described in multilamellar is laid on and adds
Fill completely on strong muscle and by described pregroove marks.
Step 4, utilizes vacuum aided to infuse resin on two prefabricated components, makes resin complete wetting two
Prefabricated component and interlayer embedded part.Utilize method that vacuum aided infuses resin on prefabricated component specifically ,' first
Dismoulding system, flow guide system, injection system and sealing system is the most jointly laid on the surface of two prefabricated components
System；Then utilize vacuum extractor to sealing system evacuation, under conditions of vacuum, utilize injection system
Resin by injection, and make the resin of injection by dismoulding system complete wetting under the guide functions of flow guide system
Two prefabricated components and interlayer embedded part.Described dismoulding system is release cloth；Described flow guide system includes flow-guiding screen
And mozzle, described mozzle is positioned at the top of described flow-guiding screen；Described sealing system include vacuum bag and
Sealant tape, described vacuum bag is bonded in large-scale sandwich structure composite material nacelle by sealant tape,
And two prefabricated components laid are sealed in vacuum bag.Utilize vacuum extractor that sealing system is taken out very
Sky, utilizes injection system resin by injection under conditions of vacuum, and makes under the guide functions of flow guide system
The resin injected is by dismoulding system complete wetting prefabricated component and interlayer embedded part.The vacuum of described sealing system
Degree≤-0.095Mpa, in pressurize one Preset Time, the pressure≤-0.075Mpa of sealing system.
Step 5, after the resin solidification injected, the surface of polishing completion so that putting down of the surface of completion
Face degree keeps consistent with the flatness of former large-scale composite material nacelle wall.Carry out after the resin solidification injected
The demoulding, the method for the demoulding specially sloughs the sealing system on prefabricated component, injection system, water conservancy diversion system successively
System and dismoulding system.
Fig. 2 is the structural representation of the completion in a kind of large-scale sandwich structure composite material nacelle aperture of the present invention
Figure, in this specific embodiment, first on specific large-scale sandwich structure composite material shelter 1 aperture
Carry out the otch in aperture, the otch in aperture according to taking off eyelid covering 120mm outside the surrounding of aperture, polish otch,
Making otch have ramped shaped, and a length of 60mm on slope, the deep of slope is degree 6mm.Then in aperture
In fill up interlayer embedded part 2, interlayer built-in fitting 2 is thinner than the bulkhead of large-scale sandwich structure composite material shelter 1
2mm, interlayer built-in fitting 2 two ends carry out chamfered, and chamfering is length 60mm, and the degree of depth is 6mm, fall
Interlayer built-in fitting surrounding is wrapped up two-layer carbon cloth as reinforcement after processing by angle.Secondly falling at interlayer embedded part 2
Prefabricated component 3 is laid in the pregroove marks of the otch formation in aperture in angle；Concrete, before laying prefabricated component 3,
First bound edge is turned to incision, and with the most fixing, then lays reinforcement, the laying of reinforcement according to
Order from narrow to wide is laid, and finally lays eyelid covering, lays eyelid covering and is prohibited from fold, bridge formation occur
And bedding void, sturdy with interlayer embedded part and nacelle inside and outside wall.Then on the eyelid covering of prefabricated component 3
Lay dismoulding system 4, flow guide system 5, injection system 6 and sealing system 7 successively；Lay flow guide system
5 are specially laying flow-guiding screen and mozzle, and flow-guiding screen is 60mm from the distance of sealing system 7, as
The relief area of glue, mozzle will be above flow-guiding screen, in order to preferably guide resin flowing；Injecting glue
The glue-feeder of system 6 to carry out rational layout, will prevent glue from directly being taken out away from sealing system 7
Walking the waste caused, the injecting glue seat of injection system is put, injecting glue distance between seats, injecting glue order, injecting glue duration
Strictly control；Sealing system 7 is that vacuum bag uses sealant tape bond to nacelle four wall, has
Need the position beaten pinch to carry out beating and scoop up, prevent the phenomenon of vacuum bag local tension.Finally utilize evacuation
Sealing system 7 is evacuated to negative pressure state by device, and vacuum need to reach below-0.095MPa, pressurize 20Min,
In pressure maintaining period, pressure must not be less than-0.075MPa, during whole evacuation, need to pay close attention to sealing system
The sealing situation of system 7, whether close inspection leaks gas, and must strictly control vacuum, otherwise be unsatisfactory for note
Adhesive tape part；After meeting injecting glue condition, resin enters flow guide system 5, along water conservancy diversion system by injection system 6
System 5 enters prefabricated component 3 and interlayer embedded part 2 by dismoulding system 4, it is achieved resin is to prefabricated component 3 and folder
The infiltration of layer embedded part 2.Hot setting is carried out again, after solidification after the resin injected first carries out normal temperature cure
Slough sealing system 7, injection system 6, flow guide system 5 and dismoulding system 6, and completion of polishing successively
Surface so that the flatness of completion keeps consistent with the flatness of former large-scale composite material nacelle wall.
The complementing method in a kind of large-scale sandwich structure composite material nacelle aperture of the present invention, is treating completion aperture
Nacelle on, use the vacuum assisted process optimized, disposably by large scale and there is special formed shelter
Aperture carry out completion, not only saved cost, the comprehensive utilization ratio of the composite nacelle of increase,
Technological operation is simple, and compensate in traditional large-scale sandwich shelter retrofit process owing to not entering
The completion of row aperture and the phenomenon scrapped, impart the new use of large-scale sandwich structure composite material shelter and use
On the way.
The foregoing is only presently preferred embodiments of the present invention, not in order to limit the present invention, all in the present invention
Spirit and principle within, any modification, equivalent substitution and improvement etc. made, should be included in this
Within bright protection domain.
Claims (10)
1. the complementing method in one kind large-scale sandwich structure composite material nacelle aperture, it is characterised in that: include
Following steps,
Step one, the surrounding in the large-scale sandwich structure composite material nacelle aperture needing completion is cut
Cut, formed and carry sloping otch, and the aperture after cutting is cleaned dried；
Step 2, puts making that match with orifice shapes and two ends in advance with the interlayer embedded part of chamfering
Put in aperture, and the chamfering at described interlayer embedded part two ends is corresponding with the otch of aperture surrounding, described folder
The chamfering at layer embedded part two ends forms the pregroove marks of two shelving structures with the otch of aperture surrounding；
Step 3, the most successively lays prefabricated component in two pregroove marks；
Step 4, utilizes vacuum aided to infuse resin on two prefabricated components, makes resin complete wetting two
Prefabricated component and interlayer embedded part；
Step 5, after the resin solidification injected, the surface of polishing completion so that putting down of the surface of completion
Face degree keeps consistent with the flatness of former large-scale composite material nacelle wall.
The completion side in a kind of large-scale sandwich structure composite material nacelle aperture the most according to claim 1
Method, it is characterised in that: the slope length range of described otch is 50mm～70mm, and slope depth bounds is
5mm～7mm.
The completion side in a kind of large-scale sandwich structure composite material nacelle aperture the most according to claim 2
Method, it is characterised in that: the chamfering length range of described interlayer embedded part is 50mm～70mm, and depth bounds is
5mm～7mm.
The completion side in a kind of large-scale sandwich structure composite material nacelle aperture the most according to claim 3
Method, it is characterised in that: the chamfering length of described interlayer embedded part is identical with the slope length of described otch, institute
The depth of chamfering stating interlayer embedded part is identical with the slope degree of depth of described otch.
5. according to the one large-scale sandwich structure composite material nacelle hole described in any one of Claims 1-4
The complementing method of mouth, it is characterised in that: in step 4, utilize vacuum aided to infuse resin into prefabricated component
On method specifically ,' first the most jointly lay dismoulding system, water conservancy diversion system on the surface of two prefabricated components
System, injection system and sealing system；Then utilize vacuum extractor to sealing system evacuation, in vacuum
Under conditions of utilize injection system resin by injection, and under the guide functions of flow guide system, make the resin of injection
By two prefabricated components of dismoulding system complete wetting and interlayer embedded part.
The completion side in a kind of large-scale sandwich structure composite material nacelle aperture the most according to claim 5
Method, it is characterised in that: in step 5, after the resin solidification injected, carry out the demoulding, the method for the demoulding
It is specially and sloughs sealing system, injection system, flow guide system and the dismoulding system on prefabricated component successively.
The completion side in a kind of large-scale sandwich structure composite material nacelle aperture the most according to claim 6
Method, it is characterised in that: described dismoulding system is release cloth；Described flow guide system includes flow-guiding screen and water conservancy diversion
Pipe, described mozzle is positioned at the top of described flow-guiding screen；Described sealing system includes vacuum bag and fluid sealant
Band, described vacuum bag is bonded in large-scale sandwich structure composite material nacelle by sealant tape, and will paving
If two prefabricated components be sealed in vacuum bag.
The completion side in a kind of large-scale sandwich structure composite material nacelle aperture the most according to claim 6
Method, it is characterised in that: the vacuum≤-0.095Mpa of described sealing system, at pressurize one Preset Time
In, the pressure≤-0.075Mpa of sealing system.
9. according to the one large-scale sandwich structure composite material nacelle hole described in any one of Claims 1-4
The complementing method of mouth, it is characterised in that: described interlayer embedded part is PVC foamed materials.
10. according to the one large-scale sandwich structure composite material nacelle described in any one of Claims 1-4
The complementing method in aperture, it is characterised in that: described prefabricated component includes reinforcement and eyelid covering, adds described in multilamellar
Strong muscle layer from narrow to wide is layered in pregroove marks, and eyelid covering described in multilamellar is laid on reinforcement and by described pre-
Groove processed is filled full.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610214057.0A CN105881931B (en) | 2016-04-07 | 2016-04-07 | A kind of complementing method in large-scale sandwich structure composite material nacelle aperture |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610214057.0A CN105881931B (en) | 2016-04-07 | 2016-04-07 | A kind of complementing method in large-scale sandwich structure composite material nacelle aperture |
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| Publication Number | Publication Date |
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| CN105881931A true CN105881931A (en) | 2016-08-24 |
| CN105881931B CN105881931B (en) | 2018-03-16 |
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Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3574924A (en) * | 1968-10-28 | 1971-04-13 | North American Rockwell | Solid state repair method and means |
| CN202848023U (en) * | 2012-07-30 | 2013-04-03 | 北京中新图锐科技有限公司 | Repairable cabin cover |
| CN202846301U (en) * | 2012-10-09 | 2013-04-03 | 洛阳双瑞风电叶片有限公司 | Ladder method repairing and grinding device for composite material wind-power blade |
| CN103802339A (en) * | 2013-08-26 | 2014-05-21 | 南京航空航天大学 | Composite material component rapid repairation device and method based on microwaves |
-
2016
- 2016-04-07 CN CN201610214057.0A patent/CN105881931B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3574924A (en) * | 1968-10-28 | 1971-04-13 | North American Rockwell | Solid state repair method and means |
| CN202848023U (en) * | 2012-07-30 | 2013-04-03 | 北京中新图锐科技有限公司 | Repairable cabin cover |
| CN202846301U (en) * | 2012-10-09 | 2013-04-03 | 洛阳双瑞风电叶片有限公司 | Ladder method repairing and grinding device for composite material wind-power blade |
| CN103802339A (en) * | 2013-08-26 | 2014-05-21 | 南京航空航天大学 | Composite material component rapid repairation device and method based on microwaves |
Non-Patent Citations (1)
| Title |
|---|
| 王振清 等: "《先进复合材料研究进展》", 31 October 2014, 哈尔滨工业大学出版社 * |
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| CN105881931B (en) | 2018-03-16 |
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