CN116922813A - Manufacturing method of aircraft wallboard and aircraft wallboard - Google Patents

Manufacturing method of aircraft wallboard and aircraft wallboard Download PDF

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Publication number
CN116922813A
CN116922813A CN202210354770.0A CN202210354770A CN116922813A CN 116922813 A CN116922813 A CN 116922813A CN 202210354770 A CN202210354770 A CN 202210354770A CN 116922813 A CN116922813 A CN 116922813A
Authority
CN
China
Prior art keywords
sacrificial layer
aircraft panel
aircraft
manufacturing
sacrificial
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.)
Pending
Application number
CN202210354770.0A
Other languages
Chinese (zh)
Inventor
卢秉贺
吴承思
王凯伦
关惟识
黄鹏
宫占峰
廉伟
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Commercial Aircraft Corp of China Ltd
Shanghai Aircraft Manufacturing Co Ltd
Original Assignee
Commercial Aircraft Corp of China Ltd
Shanghai Aircraft Manufacturing Co Ltd
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Commercial Aircraft Corp of China Ltd, Shanghai Aircraft Manufacturing Co Ltd filed Critical Commercial Aircraft Corp of China Ltd
Priority to CN202210354770.0A priority Critical patent/CN116922813A/en
Publication of CN116922813A publication Critical patent/CN116922813A/en
Pending legal-status Critical Current

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Classifications

    • 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
    • B29C70/345—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 matched moulds
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/543—Fixing the position or configuration of fibrous reinforcements before or during moulding
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/545—Perforating, cutting or machining during or after moulding
    • 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
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/10—Bulkheads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • 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
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Textile Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Laminated Bodies (AREA)

Abstract

The invention relates to the technical field of aviation processing, and discloses a manufacturing method of an aircraft wallboard and the aircraft wallboard. The method for manufacturing the aircraft panel comprises the following steps: laying prepreg in an aircraft panel mold to form an aircraft panel body; marking a high-precision matching area on the aircraft panel body; laying a sacrificial layer in the high-precision matching area, wherein the sacrificial layer comprises a plurality of sacrificial sheets which are sequentially abutted; and co-curing and forming the aircraft panel body and the sacrificial layer by adopting a co-curing and forming process to form the aircraft panel. The aircraft panel is manufactured by the method for manufacturing the aircraft panel. The manufacturing method of the aircraft wall plate is simple to operate, can effectively prevent the sacrificial layer from warping, improves the strength of the aircraft wall plate, and meets the assembly requirement of the aircraft component.

Description

Manufacturing method of aircraft wallboard and aircraft wallboard
Technical Field
The invention relates to the technical field of aviation processing, in particular to a manufacturing method of an aircraft wallboard and the aircraft wallboard.
Background
In recent years, composite structures have been widely used in the field of aviation. Because of the high flexural rigidity and axial pressure stability of composite panels, composite panels are widely used in aircraft construction for weight reduction. During aircraft assembly, certain structures require high precision fittings, and these parts involving high precision fittings require very flat tooling. For metallic materials, the mating zone can be treated by machining, but the composite part cannot be polished at will, otherwise the continuity of the fibers would be destroyed, and the strength of the part would be adversely affected. Therefore, the design of introducing the sacrificial layer in the part design process is necessary, but the sacrificial layer formed on the surface of the aircraft part at present causes abrupt structural change of the sacrificial layer area after the composite part is formed, generates larger internal stress, and generates larger warping phenomenon of the whole composite part.
Accordingly, there is a need for a method of manufacturing an aircraft panel and an aircraft panel to solve the above-mentioned problems.
Disclosure of Invention
Based on the above, the invention aims to provide a manufacturing method of an aircraft panel and the aircraft panel, which are simple to operate, can effectively prevent the sacrificial layer from warping, improve the strength of the aircraft panel and meet the assembly requirement of an aircraft component.
In order to achieve the above purpose, the invention adopts the following technical scheme:
a method of manufacturing an aircraft panel, comprising the steps of:
laying prepreg in an aircraft panel mold to form an aircraft panel body;
marking a high-precision matching area on the aircraft panel body;
laying a sacrificial layer in the high-precision matching area, wherein the sacrificial layer comprises a plurality of sacrificial sheets which are sequentially abutted;
and co-curing and forming the aircraft panel body and the sacrificial layer by adopting a co-curing and forming process to form the aircraft panel.
As a preferable mode of the method for manufacturing an aircraft panel, the sacrificial layer is cut into a plurality of the sacrificial sheets after the sacrificial layer is laid in the high-precision fitting region.
As a preferable mode of the method for manufacturing an aircraft panel, before the high-precision fitting region is laid down with the sacrificial layer, the sacrificial layer is cut to be a plurality of the sacrificial pieces, and then the plurality of the sacrificial pieces are laid down with the high-precision fitting region.
As a preferred embodiment of the method for producing an aircraft panel, the sacrificial layer and the prepreg are made of the same material.
As a preferred embodiment of the method for producing an aircraft panel, the sacrificial layer and the prepreg are both made of a carbon fiber composite material.
As a preferred embodiment of the method for producing an aircraft panel, a glue film is applied to the high-precision fitting region before the sacrificial layer is applied, and the sacrificial layer is bonded to the glue film.
As a preferred embodiment of the method for manufacturing the aircraft panel, the adhesive film is a colored adhesive film.
As a preferable mode of the method for manufacturing an aircraft panel, the sacrificial layer is annular, and the plurality of sacrificial sheets are sequentially abutted against each other to form the annular sacrificial layer.
As a preferred embodiment of the method for manufacturing an aircraft panel, the aircraft panel body and the sacrificial layer are co-cured and molded in an autoclave to form the aircraft panel.
An aircraft panel produced by the method of any one of the preceding claims.
The beneficial effects of the invention are as follows:
the invention provides a manufacturing method of an aircraft panel and the aircraft panel. When the aircraft wallboard is assembled, the sacrificial layer can be polished, so that the damage to the main body of the aircraft wallboard is avoided, the strength is damaged, and the assembly requirement of an aircraft component is met. Meanwhile, as the sacrificial layer comprises a plurality of independent sacrificial sheets, continuous long fibers are shortened, the shorter the continuous fibers are, the smaller the internal stress of the sacrificial layer in the curing process is, deformation and warping are not easy to occur, and the problem of aircraft panel sacrificial layer warping is effectively solved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the following description will briefly explain the drawings needed in the description of the embodiments of the present invention, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and other drawings may be obtained according to the contents of the embodiments of the present invention and these drawings without inventive effort for those skilled in the art.
FIG. 1 is a flow chart of a method of manufacturing an aircraft panel according to an embodiment of the present invention;
fig. 2 is a schematic structural view of an aircraft panel according to an embodiment of the present invention.
In the figure:
1. an aircraft panel body; 2. a high-precision matching region; 3. a sacrificial layer; 31. sacrificial plate.
Detailed Description
The invention is described in further detail below with reference to the drawings and examples. It is to be understood that the specific embodiments described herein are merely illustrative of the invention and are not limiting thereof. It should be further noted that, for convenience of description, only some, but not all of the structures related to the present invention are shown in the drawings.
In the present invention, unless expressly stated or limited otherwise, a first feature "above" or "below" a second feature may include both the first and second features being in direct contact, as well as the first and second features not being in direct contact but being in contact with each other through additional features therebetween. Moreover, a first feature being "above," "over" and "on" a second feature includes the first feature being directly above and obliquely above the second feature, or simply indicating that the first feature is higher in level than the second feature. The first feature being "under", "below" and "beneath" the second feature includes the first feature being directly under and obliquely below the second feature, or simply means that the first feature is less level than the second feature.
In the description of the present embodiment, the terms "upper", "lower", "left", "right", and the like are orientation or positional relationships based on those shown in the drawings, merely for convenience of description and simplicity of operation, and do not indicate or imply that the apparatus or elements referred to must have a specific orientation, be constructed and operated in a specific orientation, and thus should not be construed as limiting the invention. In the description of the present invention, unless otherwise indicated, the meaning of "a plurality" is two or more. Furthermore, the terms "first," "second," and the like, are used merely for distinguishing between descriptions and not for distinguishing between them.
As shown in fig. 1 and 2, the present embodiment provides a method for manufacturing an aircraft panel, which includes the steps of:
laying up prepreg in an aircraft panel mould to form an aircraft panel body 1;
marking a high-precision matching area 2 on the aircraft panel body 1;
laying a sacrificial layer 3 on the high-precision matching area 2, wherein the sacrificial layer 3 comprises a plurality of sacrificial sheets 31 which are abutted in turn;
the aircraft panel body 1 and the sacrificial layer 3 are co-cured to form an aircraft panel using a co-cure molding process.
The aircraft panel body 1 and the sacrificial layer 3 are co-cured and molded by adopting a co-curing molding process to obtain the aircraft panel with the sacrificial layer 3 by paving the sacrificial layer 3 on the high-precision matching area 2 of the aircraft panel body 1 formed by prepreg, and enabling the sacrificial layer 3 to comprise a plurality of sacrificial sheets 31 which are sequentially abutted. When the aircraft panel is assembled, the sacrificial layer 3 can be polished, so that the damage to the aircraft panel main body 1 is avoided, the strength is damaged, and the assembly requirement of the aircraft assembly is met. Meanwhile, as the sacrificial layer 3 comprises a plurality of independent sacrificial sheets 31, continuous long fibers are shortened, the shorter the continuous fibers are, the smaller the internal stress of the sacrificial layer 3 in the curing process is, deformation and warping are not easy to occur, and the problem of warping of the sacrificial layer 3 of the aircraft panel is effectively solved.
Specifically, the aircraft panel body 1 and the sacrificial layer 3 are co-cured in an autoclave to form an aircraft panel. The prepreg is inverted in a mold, the prepreg is soft, the sacrificial layer 3 is soft, and the sacrificial layer 3 and the prepreg are combined and then co-cured to form the hard aircraft panel.
Alternatively, the sacrificial layer 3 may be provided by cutting the sacrificial layer 3 into the plurality of sacrificial sheets 31 after the sacrificial layer 3 is laid on the high-precision fitting region 2. The sacrificial layer 3 is paved and then cut off, so that the paving precision can be improved, the position correspondence is accurate, the subsequent polishing during the assembly of the aircraft wall panel is facilitated, and the assembly precision is improved. It is also possible to cut the sacrifice layer 3 into a plurality of sacrifice pieces 31 before the sacrifice layer 3 is applied to the high-precision part 2 and then sequentially apply the plurality of sacrifice pieces 31 at the corresponding positions of the high-precision part. Firstly, the sacrificial layer 3 is cut off and then sequentially paved, so that the damage to the aircraft panel main body 1 during cutting off of the sacrificial layer 3 is avoided, the sacrificial layer 3 is also conveniently cut off, the adhesion of the sacrificial sheet 31 is avoided, the continuous long fiber of the sacrificial layer 3 is shortened, and the warping of the aircraft panel sacrificial layer 3 is avoided.
In this embodiment, the sacrificial layer 3 and the prepreg are made of the same material. The mechanical properties of the sacrificial layer 3 and the mechanical properties of the aircraft panel main body 1 are consistent, and structural abrupt changes of the sacrificial layer 3 area after the aircraft panel is molded are avoided, so that larger stress is generated, and the whole aircraft panel generates larger warping phenomenon. Preferably, both the sacrificial layer 3 and the prepreg are made of carbon fiber composite material. The sacrificial layer 3 is made of carbon fiber materials which are the same as the composite wallboard, so that the wallboard is effectively prevented from being warped due to internal force generated by inconsistent thermal expansion coefficients.
Further, before laying the sacrificial layer 3, the method further comprises the following steps:
and (3) paving an adhesive film in the high-precision matching area 2, and adhering the sacrificial layer 3 on the adhesive film.
The sacrificial layer 3 is fixed in the high-precision matching area 2 of the aircraft panel main body 1 through the adhesive film, so that the adhesive film is firmly bonded, is not easy to fall off, and is also convenient for subsequent co-curing and forming. Preferably, the adhesive film is a colored adhesive film. The colored adhesive film is adopted between the sacrificial layer 3 and the aircraft panel main body 1, so that a prompting effect is achieved, the machining phenomenon generated during machining of the sacrificial layer 3 is avoided, and the quality of each assembly of the aircraft is improved.
In this embodiment, the sacrificial layer 3 is annular, and the plurality of sacrificial sheets 31 sequentially abut against each other to form the annular sacrificial layer 3. Of course, the specific shape of the sacrificial layer 3 is set according to the required assembly process area of the aircraft panel, for example rectangular or the like.
As shown in fig. 2, the present embodiment also provides an aircraft panel manufactured by the above-described method of manufacturing an aircraft panel. When the aircraft component is assembled, the layering with a certain thickness is required to be removed, but the composite material part cannot be polished at will, otherwise the continuity of fibers is damaged, and the strength of the part is adversely affected. By arranging the sacrificial layer 3 on the surface of the aircraft panel, the sacrificial layer 3 replaces the aircraft panel, and the sacrificial layer 3 is polished, so that the aircraft panel is prevented from being damaged. And the sacrificial layer 3 in the present embodiment is divided into a plurality of sacrificial sheets 31 so that continuous long fibers become short, and the possibility of warping due to excessive internal stress is avoided, thereby ensuring the quality of the aircraft panel.
Note that the above is only a preferred embodiment of the present invention and the technical principle applied. It will be understood by those skilled in the art that the present invention is not limited to the particular embodiments described herein, but is capable of various obvious changes, rearrangements and substitutions as will now become apparent to those skilled in the art without departing from the scope of the invention. Therefore, while the invention has been described in connection with the above embodiments, the invention is not limited to the embodiments, but may be embodied in many other equivalent forms without departing from the spirit or scope of the invention, which is set forth in the following claims.

Claims (10)

1. A method of manufacturing an aircraft panel, comprising the steps of:
laying up prepreg in an aircraft panel mould to form an aircraft panel body (1);
marking a high-precision matching area (2) on the aircraft panel body (1);
laying a sacrificial layer (3) on the high-precision matching area (2), wherein the sacrificial layer (3) comprises a plurality of sacrificial sheets (31) which are sequentially abutted;
and co-curing and forming the aircraft panel main body (1) and the sacrificial layer (3) by adopting a co-curing and forming process to form the aircraft panel.
2. Method of manufacturing an aircraft panel according to claim 1, characterized in that the sacrificial layer (3) is cut into a plurality of the sacrificial sheets (31) after the high-precision fitting region (2) has been laid down with the sacrificial layer (3).
3. Method of manufacturing an aircraft panel according to claim 1, characterized in that before the high-precision fitting region (2) is laid down the sacrificial layer (3), the sacrificial layer (3) is cut off in the form of a plurality of the sacrificial sheets (31), and then a plurality of the sacrificial sheets (31) are laid down on the high-precision fitting region (2).
4. Method for manufacturing an aircraft panel according to claim 1, wherein the sacrificial layer (3) is made of the same material as the prepreg.
5. The method of manufacturing an aircraft panel according to claim 4, wherein the sacrificial layer (3) and the prepreg are each made of a carbon fiber composite material.
6. Method for manufacturing an aircraft panel according to claim 1, characterized in that a glue film is applied to the high-precision fitting area (2) before the sacrificial layer (3) is applied, the sacrificial layer (3) being glued to the glue film.
7. The method of manufacturing an aircraft panel according to claim 6, wherein the adhesive film is a colored adhesive film.
8. The method of manufacturing an aircraft panel according to claim 1, wherein the sacrificial layer (3) is annular, and a plurality of the sacrificial sheets (31) are sequentially abutted against the sacrificial layer (3) to form an annular shape.
9. The method of manufacturing an aircraft panel according to claim 1, wherein the aircraft panel body (1) and the sacrificial layer (3) are co-cured in an autoclave to form the aircraft panel.
10. An aircraft panel produced by the method of producing an aircraft panel according to any one of claims 1 to 9.
CN202210354770.0A 2022-04-06 2022-04-06 Manufacturing method of aircraft wallboard and aircraft wallboard Pending CN116922813A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN202210354770.0A CN116922813A (en) 2022-04-06 2022-04-06 Manufacturing method of aircraft wallboard and aircraft wallboard

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN202210354770.0A CN116922813A (en) 2022-04-06 2022-04-06 Manufacturing method of aircraft wallboard and aircraft wallboard

Publications (1)

Publication Number Publication Date
CN116922813A true CN116922813A (en) 2023-10-24

Family

ID=88383189

Family Applications (1)

Application Number Title Priority Date Filing Date
CN202210354770.0A Pending CN116922813A (en) 2022-04-06 2022-04-06 Manufacturing method of aircraft wallboard and aircraft wallboard

Country Status (1)

Country Link
CN (1) CN116922813A (en)

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