CN208452345U - A kind of molding die of technique for aircraft composite siding - Google Patents
A kind of molding die of technique for aircraft composite siding Download PDFInfo
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- CN208452345U CN208452345U CN201820973629.8U CN201820973629U CN208452345U CN 208452345 U CN208452345 U CN 208452345U CN 201820973629 U CN201820973629 U CN 201820973629U CN 208452345 U CN208452345 U CN 208452345U
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- siding
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- reinforcing rib
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Abstract
A kind of molding die of technique for aircraft composite siding, the siding is made of the reinforcing rib of covering and protrusion, molding die includes upper die and lower die, there is paving face corresponding with skin shape surface in upper mold lower surface, the thick item of control corresponding with skin thickness is equipped in the periphery in paving face, the lower die contains lower die holder and lower mold body, the upper surface of lower mold body is additionally provided with groove corresponding with siding reinforcing rib, separately have and the embeddable groove of the matched movable abaculus of siding reinforcing rib, by in the corresponding groove of reinforcing rib insertion lower mold body of preforming, fixed with corresponding movable abaculus；The paving covering on the paving face of upper mold, and bag making vacuumizes compacting；Thick item will be controlled to be placed between upper die body and lower mold body, and molded upper die body and lower mold body positioning by location hole with positioning pin, and the laggard solidification of hot-press tank molding of vacuum bag processed.
Description
Technical field
This application involves composite molding field, specifically a kind of shaping mould suitable for technique for aircraft composite siding
Tool.
Background technique
With the development of composite material, multiple material product proportion on aviation aircraft is increasing, in order to adapt to city
Development and improve itself competitiveness, aircraft manufacturing has been unsatisfactory for only producing simple covering, beam, rib, stringer class
Small size part.And can develop large-sized integral reinforced wall panel parts becomes the symbol of each supplier's comprehensive strength.Because
Wall strength, rigidity not only can be improved in this large scale integration Material Stiffened Panel, reduces fastener quantity, reduces connector, also
A large amount of assembly times can be saved, several or even tens parts are reduced into a part, construction weight is significantly mitigated
Manufacturing cost is reduced simultaneously.
It is answered in unidirectional (course or the open up to) Material Stiffened Panel of material in large scale, two-way Material Stiffened Panel is as typical aviation in length and breadth
Product structure type represents the highest level of current Composite Material Stiffened Panel.Its maximum feature is the whole strong of structure
Degree, connects less, is light-weight good rigidity, but structure is complicated for forming frock, therefore urgently a kind of new tool structure of researching and designing comes
Two-way Material Stiffened Panel in length and breadth is formed, traditional type portal frame positioning method is avoided to do in the positioning of rib intersectional region, the mutual of bag making
It relates to, reduces the quantity of tooling attachment, while avoiding the unevenness of rib intersectional region pressure transmission in length and breadth.This structure tooling can be disposable
The solidification by cement for completing reinforcing rib and covering in length and breadth, has effectively saved manufacturing cost, has reduced because repeatedly bringing big ruler into tank
The risk of very little integral reinforced wall panel parts performance decline.
Summary of the invention
The application be designed to provide a kind of technique for aircraft composite siding it is hot-forming used in molding die, use
In realization, two-way reinforcing rib and covering are glued one-step solidification in length and breadth.It reduces because repeatedly solidifying bring cost, effectively solves
The positioning of traditional type portal frame leads to the quality such as reinforcing rib intersectional region bring pressure transmission in length and breadth is uneven, reinforcing rib position is overproof
Problem.
A kind of molding die of technique for aircraft composite siding, the siding are made of the reinforcing rib of covering and protrusion, feature
Be: the molding die includes upper die and lower die, and there is paving face corresponding with skin shape surface in the upper mold lower surface,
The periphery in paving face is equipped with the thick item of control corresponding with skin thickness, location hole is additionally provided in upper mold, under the lower die contains
Die holder and lower mold body, lower mold body are located on lower die holder, and the upper surface of lower mold body is matched with siding lower surface, the upper surface of lower mold body
Be additionally provided with groove corresponding with siding reinforcing rib, separately have with the matched movable embeddable groove of abaculus of siding reinforcing rib, in lower die
Location hole corresponding with upper die body is additionally provided on body.
In use, connecting reinforcing rib with covering in the corresponding groove of reinforcing rib insertion lower mold body of preforming
Surface flushes with the upper surface of lower mold body or within the scope of tolerance, and is fixed with corresponding movable abaculus；In the paving of upper mold
Composite material paving covering is used on veneer, and bag making vacuumizes compacting；Thick item will be controlled to be placed between upper die body and lower mold body, be used in combination
Positioning pin is molded upper die body and lower mold body positioning by location hole, and the laggard solidification of hot-press tank molding of vacuum bag processed.
The beneficial effect of the application is to provide large scale and steps up the disposable cementation solidifying forming method of siding in length and breadth, in design
Mould, lower die assembled tool when not only can guarantee the surface quality and solidification in siding aerodynamic configuration face pressure uniformly transfer, but also can control
The thickness of covering processed, while it being able to achieve the precise positioning of covering and reinforcing rib again.
Attached drawing is described in further detail this application with reference to embodiments.
Detailed description of the invention
Fig. 1 is technique for aircraft composite wall panel structure schematic diagram.
Fig. 2 is the forming die structure schematic diagram of technique for aircraft composite siding.
Fig. 3 is the forming method signal for the technique for aircraft composite siding that reinforcing rib is T shape.
Fig. 4 is the forming method signal for the technique for aircraft composite siding that reinforcing rib is J-shaped.
Fig. 5 is the forming method signal for the technique for aircraft composite siding that reinforcing rib is H-shaped.
Explanation: 1 covering, 2 reinforcing ribs, 3 upper molds, 4 lower dies, 5 lower mold bodies, 6 lower die holders, 7 movable abaculus, 8 is numbered in attached drawing
Control thick item, 9 pins.
Specific embodiment
Referring to attached drawing, this application involves technique for aircraft composite siding be distributed on covering by covering 1 and longitudinally, laterally
Reinforcing rib 2 forms.The technique for aircraft composite wallboard forming mold that the application proposes includes upper mold 3 and lower die 4, the upper mold 3
Lower surface have paving face corresponding with skin shape surface, be equipped with corresponding with skin thickness control thickness item in the periphery in paving face
8, location hole is additionally provided in upper mold 3, the lower die 4 contains lower die holder 6 and lower mold body 5, and lower mold body 5 is located on lower die holder 6,
The upper surface of lower mold body 5 is matched with siding lower surface, and the upper surface of lower mold body 5 is additionally provided with groove corresponding with siding reinforcing rib
10, separately have with the embeddable groove 10 of the matched movable abaculus 7 of siding reinforcing rib 2, be additionally provided in lower mold body 5 corresponding with upper die body
Location hole.
When wallboard forming, the reinforcing rib 2 of preparatory individually curing molding siding, to the reinforcing rib digital control milling after demoulding to most
Whole outer dimension；Reinforcing rib shape in implementation can be T shape, H-shaped, J-shaped etc., and reinforcing rib of different shapes corresponds to different
Movable abaculus 7, replacing different movable abaculus can be used for positioning the reinforcing rib of different cross section size, and the effect of movable abaculus is exactly
Reinforcing rib is pressed abd fixed in the groove 10 of lower mold body, after wallboard forming is complete, separates siding with molding die, then activity
Abaculus takes out.
By in the reinforcing rib insertion corresponding groove 10 of lower mold body 5 of preforming, positioned with corresponding movable abaculus 7 solid
Fixed, the upper surface for connecting reinforcing rib 2 with covering 1 is flush to the upper surface of lower mold body or within the scope of tolerance.
Composite material paving covering 1 is used on the paving face of upper mold 3, and bag making vacuumizes compacting；
Thick item 8 will be controlled to be placed between upper mold 3 and lower mold body 5, and pass through location hole for upper mold 3 and lower mold body 5 with positioning pin 9
Positioning molding, and the laggard solidification of hot-press tank molding of vacuum bag processed.
The Material Stiffened Panel two-way in length and breadth that this forming method is glued altogether suitable for dead size reinforcing rib after curing molding and covering.
Movable abaculus support cooperation reinforcing rib is fixedly mounted in the groove 10 of lower mold body 5, and covering 1 utilizes after the completion of 3 paving of upper mold
Shop bolt 9 completes the accurate positionin with lower mold body 5, and the uniform pressure transmission of upper mold 3 during solidification by cement guarantees matter inside siding
Amount, and two-way reinforcing rib 2 solidification bonding with covering 1 in length and breadth, control thick item 8 between upper mold 3 and lower mold body 5, guarantee wall
The thickness requirement of plate covering.This structure tooling is also applied for curved surface covering, when covering be curved surface when, upper mold 3, lower mold body 5 and
Movable abaculus 7 is corresponding surface.
Claims (1)
1. a kind of molding die of technique for aircraft composite siding, the siding are made of the reinforcing rib of covering and protrusion, feature exists
In: the molding die includes upper die and lower die, and there is paving face corresponding with skin shape surface in the upper mold lower surface, is being spread
The periphery of veneer is equipped with the thick item of control corresponding with skin thickness, location hole is additionally provided in upper mold, the lower die contains lower die
Seat and lower mold body, lower mold body are located on lower die holder, and the upper surface of lower mold body is matched with siding lower surface, and the upper surface of lower mold body is also
Equipped with groove corresponding with siding reinforcing rib, separately have with the matched movable embeddable groove of abaculus of siding reinforcing rib, in lower mold body
On be additionally provided with location hole corresponding with upper die body.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820973629.8U CN208452345U (en) | 2018-06-22 | 2018-06-22 | A kind of molding die of technique for aircraft composite siding |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820973629.8U CN208452345U (en) | 2018-06-22 | 2018-06-22 | A kind of molding die of technique for aircraft composite siding |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208452345U true CN208452345U (en) | 2019-02-01 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201820973629.8U Active CN208452345U (en) | 2018-06-22 | 2018-06-22 | A kind of molding die of technique for aircraft composite siding |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108688196A (en) * | 2018-06-22 | 2018-10-23 | 西安飞机工业（集团）有限责任公司 | A kind of forming method and molding die of technique for aircraft composite siding |
| CN111590794A (en) * | 2020-05-22 | 2020-08-28 | 西安飞机工业（集团）有限责任公司 | Composite material T-shaped reinforced wall plate autoclave forming die structure and forming method |
| CN113103477A (en) * | 2021-04-06 | 2021-07-13 | 湖南山河科技股份有限公司 | Large aircraft fuselage forming die |
| CN113977983A (en) * | 2021-10-15 | 2022-01-28 | 江西洪都航空工业集团有限责任公司 | Rib positioning device and method for composite material wallboard structural member |
-
2018
- 2018-06-22 CN CN201820973629.8U patent/CN208452345U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108688196A (en) * | 2018-06-22 | 2018-10-23 | 西安飞机工业（集团）有限责任公司 | A kind of forming method and molding die of technique for aircraft composite siding |
| CN111590794A (en) * | 2020-05-22 | 2020-08-28 | 西安飞机工业（集团）有限责任公司 | Composite material T-shaped reinforced wall plate autoclave forming die structure and forming method |
| CN113103477A (en) * | 2021-04-06 | 2021-07-13 | 湖南山河科技股份有限公司 | Large aircraft fuselage forming die |
| CN113103477B (en) * | 2021-04-06 | 2023-02-28 | 湖南山河科技股份有限公司 | Large aircraft fuselage forming die |
| CN113977983A (en) * | 2021-10-15 | 2022-01-28 | 江西洪都航空工业集团有限责任公司 | Rib positioning device and method for composite material wallboard structural member |
| CN113977983B (en) * | 2021-10-15 | 2023-06-30 | 江西洪都航空工业集团有限责任公司 | Rib positioning device and method for composite material wallboard structural member |
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