CN114368469A - Airplane airfoil composite material wing tip structure and manufacturing method - Google Patents
Airplane airfoil composite material wing tip structure and manufacturing method Download PDFInfo
- Publication number
- CN114368469A CN114368469A CN202011115037.0A CN202011115037A CN114368469A CN 114368469 A CN114368469 A CN 114368469A CN 202011115037 A CN202011115037 A CN 202011115037A CN 114368469 A CN114368469 A CN 114368469A
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- China
- Prior art keywords
- foam core
- wing tip
- core
- wingtip
- integral
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- 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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Links
- 239000002131 composite material Substances 0.000 title claims abstract description 25
- 238000004519 manufacturing process Methods 0.000 title claims description 9
- 239000006260 foam Substances 0.000 claims abstract description 78
- 238000005192 partition Methods 0.000 claims abstract description 20
- 229920005989 resin Polymers 0.000 claims abstract description 14
- 239000011347 resin Substances 0.000 claims abstract description 14
- 238000003754 machining Methods 0.000 claims description 12
- 239000008358 core component Substances 0.000 claims description 9
- 239000011248 coating agent Substances 0.000 claims description 6
- 238000000576 coating method Methods 0.000 claims description 6
- 210000001503 joint Anatomy 0.000 claims description 6
- 238000000465 moulding Methods 0.000 claims description 6
- 239000000463 material Substances 0.000 claims description 5
- 238000004026 adhesive bonding Methods 0.000 claims description 4
- 238000005253 cladding Methods 0.000 claims description 2
- 239000002184 metal Substances 0.000 description 3
- 238000000034 method Methods 0.000 description 3
- 239000000306 component Substances 0.000 description 2
- 229920001342 Bakelite® Polymers 0.000 description 1
- 239000000853 adhesive Substances 0.000 description 1
- 230000001070 adhesive effect Effects 0.000 description 1
- 239000004637 bakelite Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007688 edging Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 230000002427 irreversible effect Effects 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229910052755 nonmetal Inorganic materials 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
- 238000007493 shaping process Methods 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
Abstract
The wing tip structure is connected with an airplane wing face box section, and comprises a skin, a foam core, an end partition board and a tail edge strip, wherein the foam core is a variable cross-section machine addition structure matched with the appearance of the wing tip, one side of the foam core is connected with the end partition board, the other side of the foam core is connected with the tail edge strip, the end partition board and the tail edge strip are composite prefabricated products, the foam core, the end partition board and the tail edge strip are bonded to form a whole wing tip core structure, and the skin is a resin skin coated on the outer layer of the wing tip core structure.
Description
Technical Field
The application relates to the technical field of airplane design and manufacture, in particular to an airplane airfoil composite wingtip structure and a manufacturing method thereof.
Background
The wings of an airplane can be divided into structures such as wing boxes, fixed front edges, fixed rear edges, wing tips, nacelle hangers, flaps, ailerons, spoilers and the like according to parts.
In the prior art, in order to improve the rigidity of the skin and maintain the aerodynamic shape, the wing tip structure of the airplane airfoil is generally a metal structure, and frameworks such as beams, clapboards and the like are arranged in the skin. The structure has the advantages that the number of parts and connecting pieces is large, the structure weight is greatly increased, the process forming difficulty of the skin and skeleton structure is greatly increased for the airfoil with a complex appearance, such as a hyperboloid, the requirements on structural maintainability and interchangeability are reduced, the use performance of the airplane is influenced to a certain extent, and the service life of the airplane is shortened. At present, composite materials are widely applied to important parts such as fuselages and wings, and compared with metal structures, the composite material structure greatly reduces the weight of the structure while meeting the use performance of an airplane. At present, the wing tip structure of the airplane wing surface is mainly formed by mechanically connecting a composite material skin and a metal framework, under the condition, a large number of fasteners are used, irreversible damage is caused to the composite material structure, the maintainability and the reliability of the airplane are influenced, and the structure weight is greatly increased.
Disclosure of Invention
In view of the shortcomings of the prior art, it is an object of the present application to provide an aircraft airfoil wing composite tip structure and method of manufacture.
The utility model provides an aircraft wing face class combined material wing tip structure, this wing tip structure is connected with aircraft wing face box section, the wing tip structure contain covering, foam core, end baffle, tail strake, its characterized in that, the foam core be a variable cross section machine addition type structure who matches with the wing tip appearance, a side connection end baffle of foam core, the tail strake is connected to the opposite side of foam core, end baffle and tail strake be the combined material prefab, foam core, end baffle and tail strake bond and form holistic wing tip core structure, the covering be the resin covering of cladding at wing tip core structure skin.
The foam core can be a combined structure spliced by butt joint surfaces, one or more lightening blind holes are arranged on the butt joint surfaces of the foam core, another vent hole communicated with the lightening blind holes is arranged on the butt joint surfaces of the foam core, the vent hole is communicated to the surface of the foam core, a corresponding vent hole is arranged on the end partition plate, and the vent hole is communicated with the lightening blind holes of the foam core through the vent hole of the foam core.
The application also provides a manufacturing method of the aircraft airfoil composite tip structure, which is characterized by comprising the following steps: 1) according to a design digifax of a wing tip structure, firstly, an end clapboard and a tail edge strip are pre-cured and molded in a resin paving and pasting mode; 2) machining the foam core structure in a machining mode; 3) bonding the foam core structure with the end partition plate and the tail edge strip to form an integral wingtip core structure; 4) and taking the integral wingtip core structure as a mold, coating resin skins on the outer side of the wingtip core structure, and carrying out integral co-gluing molding on the wingtip structure.
When the foam core is a combined structure spliced by the abutting surfaces, when the foam core structure is processed in a machining mode, firstly, two foam core components are processed in the machining mode, and a lightening blind hole and an air vent are processed on the abutting surfaces of the foam core components; then the two foam core components are butted to form an integral foam core structure with a wing tip structure; air holes corresponding to the air holes are processed on the end clapboard; bonding the integral foam core structure, the end partition plate and the tail edge strip into an integral wingtip core structure, so that the air holes in the end partition plate are communicated with the air holes and the lightening blind holes of the foam core; and finally, taking the integral wingtip core structure as a mold, coating resin skins on the outer side of the wingtip core structure, and carrying out integral co-bonding molding on the wingtip structure.
The beneficial effect of this application lies in: 1) the integrated structure is favorable for the application of composite materials, and the skin, the end clapboard, the foam core and the tail edge strip are glued together and integrally formed, so that the process difficulty is reduced, and the number of parts and firmed parts is reduced. 2) Adopt the foam core to fill in the covering, and be equipped with and alleviate the blind hole, improved the rigidity of covering, strengthened structural stability, simultaneously, because foam core density is less, consequently, by a wide margin alleviate structural weight. 3) The foam core is provided with the vent holes which are communicated with the vent holes in the end partition plate, so that when the high-temperature curing co-bonding molding is carried out, gas in the lightening blind holes can be conducted to the outside of the wing tip, the expansion of high-temperature gas is avoided, the overall performance of the foam core is improved, and the overall use performance of the wing tip is further improved. 4) The C-shaped design of the end partition board ensures that the end partition board has enough adhesive strength with the inner surface of the skin and the foam core, and improves the bearing capacity. 5) The wing tip structure is a full-gluing structure, holes do not need to be formed in the composite material component, damage to the performance of the composite material is reduced, the stress concentration phenomenon on the component is relieved, and the fatigue performance of the airplane is greatly improved.
The present application is described in detail below with reference to the attached drawings.
Drawings
FIG. 1 is a schematic view of the structure of an aircraft airfoil composite tip of the present application
FIG. 2 is a schematic cross-sectional view of the aircraft airfoil composite tip structure of the present application
FIG. 3 is a schematic view of the bonding of the foam core, the tail strip and the skin.
The numbering in the figures illustrates: 1 wingtip structure, 2 skins, 3 end clapboards, 4 tail edgings, 5 foam cores, 6 butt-joint surfaces, 7 lightening blind holes, 8 vent holes and 9 vent holes.
DETAILED DESCRIPTION OF EMBODIMENT (S) OF INVENTION
Referring to the attached drawings, the wing tip structure 1 of the aircraft wing composite material of the application is connected with an aircraft wing box, the wing tip structure 1 comprises a skin 2, a foam core 5, an end baffle plate 3 and a tail edge strip 4, in implementation, the foam core 5 is a variable cross-section machining structure matched with the appearance of the wing tip, the foam core 5 is filled in the skin 2 and is coated by the skin 2, one side of the foam core 5 is connected with the end baffle plate 3, the other side of the foam core 5 is connected with the tail edge strip 4, the end baffle plate 3 and the tail edge strip 4 are composite material prefabricated products, the foam core 5, the end baffle plate 3 and the tail edge strip 4 are bonded to form an integral wing tip core structure, and the skin 1 is a resin skin coated on the outer layer of the wing tip core structure.
In the implementation, in order to reduce the structural weight to the maximum extent, the foam core 5 is a combined structure spliced by butt joint surfaces 6, one or more lightening blind holes 7 are further arranged on the butt joint surfaces of the foam core 6, a vent hole 8 communicated with the lightening blind holes 7 is communicated to the surface of the foam core 5, a corresponding vent hole 9 is arranged on the end partition plate 4, and the vent hole 9 is communicated with the lightening blind holes 7 of the foam core through the vent hole 8 of the foam core. Be equipped with air vent 8 on the foam core, with the last bleeder vent 9 intercommunication of end baffle, when the high temperature curing joint shaping, can will alleviate the gas in the blind hole 7 and switch on the wing tip outside, avoid high-temperature gas inflation to influence wing tip structure appearance, improved the wholeness ability of foam core, and then improved the holistic performance of wing tip.
The diameter of the air holes on the end clapboard is larger than that of the air holes on the foam core. In the embodiment, the diameter of the vent hole 9 on the end clapboard is 4 mm-5 mm larger than that of the vent hole 8 on the foam core.
The aircraft airfoil composite tip structure comprises the following contents in the manufacturing process: firstly, according to a design digifax of a wing tip structure, an end clapboard and a tail edge strip are pre-cured and molded by adopting a resin paving and pasting mode; the upper end and the lower end of the end clapboard 3 are used for supporting skins, one side of the end clapboard is used for bonding foam cores and sealing the end structure of the foam cores, and the section of the end clapboard is C-shaped. It is emphasized that the cross-section of the baffle may also be in other forms, such as "I" or "Z" form, with the trailing edge strip also serving to support the skin and seal the tail structure of the foam core. It should be emphasized that the tail strip is formed by resin coating and curing, but is not limited to this composite material form, and may be other non-metal material forms, such as cloth-sandwiched bakelite.
The foam core is processed in a machining mode, when the foam core is a combined structure formed by splicing abutting surfaces 6, two foam core components are processed in the machining mode firstly, and lightening blind holes 7 and vent holes 8 are processed on the abutting surfaces 6 of the foam core components; then the two foam core components are butted to form an integral foam core structure with a wing tip structure; air holes 9 corresponding to the air holes 8 are processed on the end partition plate 4, and the air holes can be reserved when the end partition frame is prefabricated. Bonding the integral foam core 3 structure with the end partition plate 3 and the tail edge strip 4 to form an integral wing tip core structure, and communicating the air holes 9 on the end partition plate 3 with the air holes 8 of the foam core 3 and the lightening blind holes 7; and finally, taking the integral wingtip core structure as a mold, coating resin skins on the outer side of the wingtip core structure, and carrying out integral co-bonding molding on the wingtip structure.
The structure reduces the number of connecting pieces, reduces the material damage and stress concentration caused by hole making on the composite material member, improves the fatigue performance of the airplane, and further improves the structural efficiency and the use quality of the airplane.
Claims (5)
1. The utility model provides an aircraft wing face class combined material wing tip structure, this wing tip structure is connected with aircraft wing face box section, the wing tip structure contain covering, foam core, end baffle, tail strake, its characterized in that, the foam core be a variable cross section machine addition type structure who matches with the wing tip appearance, a side connection end baffle of foam core, the tail strake is connected to the opposite side of foam core, end baffle and tail strake be the combined material prefab, foam core, end baffle and tail strake bond and form holistic wing tip core structure, the covering be the resin covering of cladding at wing tip core structure skin.
2. The aircraft airfoil composite tip structure of claim 1, wherein said foam core is a composite structure assembled by abutting surfaces, one or more lightening blind holes are formed in the abutting surfaces of the foam core, another vent hole communicated with the lightening blind holes is communicated to the surface of the foam core, and a corresponding vent hole is formed in the end partition plate and communicated with the lightening blind holes of the foam core through the vent hole of the foam core.
3. The aircraft airfoil composite tip structure of claim 2, wherein said end bulkhead air holes are of a larger diameter than the air holes in the foam core.
4. A method of manufacturing an aircraft airfoil composite tip structure according to claim 1, comprising: 1) according to a design digifax of a wing tip structure, firstly, an end clapboard and a tail edge strip are pre-cured and molded in a resin paving and pasting mode; 2) machining the foam core structure in a machining mode; 3) bonding the foam core structure with the end partition plate and the tail edge strip to form an integral wingtip core structure; 4) and taking the integral wingtip core structure as a mold, coating resin skins on the outer side of the wingtip core structure, and carrying out integral co-gluing molding on the wingtip structure.
5. A method of manufacturing an aircraft airfoil composite tip structure according to claim 2, comprising: 1) according to a design digifax of a wing tip structure, firstly, an end clapboard and a tail edge strip are pre-cured and molded in a resin paving and pasting mode; 2) machining two foam core components in an machining mode, and machining lightening blind holes and vent holes on the butt joint surfaces of the foam core components; 3) butting the two foam core components to form an integral foam core structure of a wing tip structure; 4) air holes corresponding to the air holes are processed on the end partition plate; 5) bonding the integral foam core structure with the end partition plate and the tail edge strip to form an integral wingtip core structure; 6) and taking the integral wingtip core structure as a mold, coating resin skins on the outer side of the wingtip core structure, and carrying out integral co-gluing molding on the wingtip structure.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011115037.0A CN114368469A (en) | 2020-10-16 | 2020-10-16 | Airplane airfoil composite material wing tip structure and manufacturing method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011115037.0A CN114368469A (en) | 2020-10-16 | 2020-10-16 | Airplane airfoil composite material wing tip structure and manufacturing method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114368469A true CN114368469A (en) | 2022-04-19 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202011115037.0A Pending CN114368469A (en) | 2020-10-16 | 2020-10-16 | Airplane airfoil composite material wing tip structure and manufacturing method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114368469A (en) |
Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5806796A (en) * | 1995-03-04 | 1998-09-15 | British Aerospace Public Limited Company | Composite laminate |
| CN2692747Y (en) * | 2003-10-10 | 2005-04-13 | 山西大学 | Teaching electronic board |
| CN201999199U (en) * | 2011-03-15 | 2011-10-05 | 成都飞机设计研究所 | Novel light wingtip winglet structure for unmanned aerial vehicles |
| CN102448816A (en) * | 2009-04-01 | 2012-05-09 | 空中客车德国运营有限责任公司 | Fuselage segment, and method for the production of a fuselage segment |
| CN204822056U (en) * | 2015-05-25 | 2015-12-02 | 中国航天空气动力技术研究院 | Combined material aileron structure |
| CN205099710U (en) * | 2015-10-15 | 2016-03-23 | 安徽鑫海环保新材料股份有限公司 | Novel KR stirring rake steel of structure constructs |
| CN107152311A (en) * | 2017-05-27 | 2017-09-12 | 中国航发湖南动力机械研究所 | The turbine disk, engine and aircraft |
| CN209274884U (en) * | 2018-11-07 | 2019-08-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full composite material rudder face foam trailing edge structures |
| CN111688904A (en) * | 2019-03-13 | 2020-09-22 | 空中客车营运有限公司 | Aircraft wing component |
-
2020
- 2020-10-16 CN CN202011115037.0A patent/CN114368469A/en active Pending
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5806796A (en) * | 1995-03-04 | 1998-09-15 | British Aerospace Public Limited Company | Composite laminate |
| CN2692747Y (en) * | 2003-10-10 | 2005-04-13 | 山西大学 | Teaching electronic board |
| CN102448816A (en) * | 2009-04-01 | 2012-05-09 | 空中客车德国运营有限责任公司 | Fuselage segment, and method for the production of a fuselage segment |
| CN201999199U (en) * | 2011-03-15 | 2011-10-05 | 成都飞机设计研究所 | Novel light wingtip winglet structure for unmanned aerial vehicles |
| CN204822056U (en) * | 2015-05-25 | 2015-12-02 | 中国航天空气动力技术研究院 | Combined material aileron structure |
| CN205099710U (en) * | 2015-10-15 | 2016-03-23 | 安徽鑫海环保新材料股份有限公司 | Novel KR stirring rake steel of structure constructs |
| CN107152311A (en) * | 2017-05-27 | 2017-09-12 | 中国航发湖南动力机械研究所 | The turbine disk, engine and aircraft |
| CN209274884U (en) * | 2018-11-07 | 2019-08-20 | 中国航空工业集团公司西安飞机设计研究所 | A kind of full composite material rudder face foam trailing edge structures |
| CN111688904A (en) * | 2019-03-13 | 2020-09-22 | 空中客车营运有限公司 | Aircraft wing component |
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