WO2021032150A1 - 模具、组装预成型结构的制造方法和壁板结构的制造方法 - Google Patents

模具、组装预成型结构的制造方法和壁板结构的制造方法 Download PDF

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Publication number
WO2021032150A1
WO2021032150A1 PCT/CN2020/110183 CN2020110183W WO2021032150A1 WO 2021032150 A1 WO2021032150 A1 WO 2021032150A1 CN 2020110183 W CN2020110183 W CN 2020110183W WO 2021032150 A1 WO2021032150 A1 WO 2021032150A1
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Prior art keywords
mold
shaped
shaped long
long truss
base
Prior art date
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PCT/CN2020/110183
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English (en)
French (fr)
Inventor
丛晶洁
李星
王亦凡
温顺达
吴德财
徐东明
Original Assignee
中国商用飞机有限责任公司北京民用飞机技术研究中心
中国商用飞机有限责任公司
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Application filed by 中国商用飞机有限责任公司北京民用飞机技术研究中心, 中国商用飞机有限责任公司 filed Critical 中国商用飞机有限责任公司北京民用飞机技术研究中心
Priority to EP20855278.6A priority Critical patent/EP4019220A4/en
Publication of WO2021032150A1 publication Critical patent/WO2021032150A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/0003—Producing profiled members, e.g. beams
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
    • B29B11/00—Making preforms
    • B29B11/06—Making preforms by moulding the material
    • 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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/30—Mounting, exchanging or centering
    • B29C33/301—Modular mould systems [MMS], i.e. moulds built up by stacking mould elements, e.g. plates, blocks, rods
    • 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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/30—Mounting, exchanging or centering
    • B29C33/305—Mounting of moulds or mould support plates
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/70—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor by 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/001—Joining in special atmospheres
    • B29C66/0012—Joining in special atmospheres characterised by the type of environment
    • B29C66/0014—Gaseous environments
    • B29C66/00145—Vacuum, e.g. partial vacuum
    • 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
    • B29C70/34—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
    • B29C70/40—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
    • B29C70/446—Moulding structures having an axis of symmetry or at least one channel, e.g. tubular structures, frames
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29D—PRODUCING PARTICULAR ARTICLES FROM PLASTICS OR FROM SUBSTANCES IN A PLASTIC STATE
    • B29D99/00—Subject matter not provided for in other groups of this subclass
    • B29D99/001—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings
    • B29D99/0014—Producing wall or panel-like structures, e.g. for hulls, fuselages, or buildings provided with ridges or ribs, e.g. joined ribs
    • 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
    • B29C33/00—Moulds or cores; Details thereof or accessories therefor
    • B29C33/38—Moulds or cores; Details thereof or accessories therefor characterised by the material or the manufacturing process
    • B29C33/3842—Manufacturing moulds, e.g. shaping the mould surface by machining
    • B29C2033/385—Manufacturing moulds, e.g. shaping the mould surface by machining by laminating a plurality of layers
    • 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
    • B29C2791/00—Shaping characteristics in general
    • B29C2791/004—Shaping under special conditions
    • B29C2791/006—Using vacuum
    • 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
    • B29L2031/3082—Fuselages
    • 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

Definitions

  • This application relates to the technical field of aviation manufacturing, for example, to a mold, a manufacturing method of an assembled preformed structure, and a manufacturing method of a wall panel structure.
  • Composite materials are widely used in the aerospace field because of their high specific stiffness, strong designability, and easy integral molding.
  • composite materials have been used as wing skins (also known as wing panels), fuselages, horizontal tails, ailerons, vertical tails, sidewall panels, bulkheads, wing ribs and stiffeners.
  • Bearing member also known as wing panels
  • wall panels with T-shaped and U-shaped long trusses as stiffeners are widely used in the main bearing structure of the fuselage.
  • the current U-shaped long truss unit layup molds are mostly all-steel dies for right-angle profiles.
  • the T-shaped long truss wall structure has a relatively small bonding area between the bottom layer and the skin of the long truss, and the long truss is easy to be degummed, which affects the quality of the entire siding structure.
  • the layup of the long truss units on both sides is removed from the stacking tooling and transferred to the curing tooling and needs to be repositioned and assembled.
  • the accuracy is not easy to guarantee, and the process is cumbersome and complicated. Influencing the positioning accuracy of the long stringer axis, it is easy to appear that the long stringer axis and straightness do not meet the requirements. At the same time, the surface quality of the parts is not good.
  • This application proposes a U-shaped long stringer pre-forming mold, which reduces mold manufacturing costs, indirectly improves the efficiency of the U-shaped prepreg layer on the skin layer, and improves the corners of the long stringer The quality guarantees the quality and precision of the products and simplifies the process.
  • This application proposes a method for manufacturing a U-shaped long truss assembly pre-formed structure.
  • the manufacturing method improves the layup efficiency of the U-shaped prepreg layer on the skin layer, reduces the mold manufacturing cost, and improves the length
  • the quality of the corners of the stringer ensures the quality and accuracy of the product and simplifies the process.
  • This application proposes a method for manufacturing a U-shaped long truss wall panel structure.
  • the manufacturing method improves the layup efficiency of the U-shaped prepreg layer on the skin layer, reduces the mold manufacturing cost, and improves the long truss
  • the quality at the corner ensures the quality and precision of the product and simplifies the process.
  • An embodiment provides a mold for preforming a U-shaped long truss, including a base, a rigid mold, and an elastic mold; the rigid mold is detachably placed on the base, and the rigid mold has a U-shaped structure, and The rigid mold is wrapped on the three adjacent outer side walls of the base; the elastic mold is placed on the rigid mold, the elastic mold has a U-shaped structure, and the elastic mold is wrapped on the The outer wall surface of the rigid mold.
  • An embodiment provides a method for manufacturing a U-shaped long truss assembly pre-formed structure, using the above-mentioned U-shaped long truss pre-forming mold, and the method includes:
  • a plurality of U-row long truss preformed structures are distributed in a horizontal direction, and an intermediate interlayer is placed between two adjacent U-shaped long truss preformed structures.
  • An embodiment provides a method for manufacturing a U-shaped long truss wall panel structure.
  • the U-shaped long truss assembly preformed structure manufactured by the above method includes:
  • the U-shaped long truss assembly preformed structure after the base is removed is rotated 180 degrees and placed on the skin ply;
  • Fig. 1 is a schematic structural diagram of a U-shaped long truss pre-forming mold provided by the specific embodiment of the present application;
  • Fig. 2 is a schematic structural diagram of a U-shaped long truss assembly preformed structure provided by a specific embodiment of the present application;
  • FIG. 3 is a schematic diagram of the U-shaped long truss wall panel structure provided by the specific embodiment of the present application when the rigid mold, the elastic mold and the skin tooling are not disassembled;
  • FIG. 4 is a schematic structural diagram of a U-shaped long truss wall panel structure provided by a specific embodiment of the present application.
  • FIG. 5 is a flowchart of a manufacturing method of a U-shaped long truss assembly pre-formed structure provided by a specific embodiment of the present application;
  • Fig. 6 is a flowchart of a manufacturing method of a U-shaped long truss wall structure provided by a specific embodiment of the present application.
  • the U-shaped long truss pre-forming mold in the present application includes a base 1, a rigid mold 2 and an elastic mold 3.
  • the rigid mold 2 is detachably placed on the base 1, the rigid mold 2 has a U-shaped structure, and the rigid mold 2
  • the elastic mold 3 is placed on the rigid mold 2, the elastic mold 3 has a U-shaped structure, and the elastic mold 3 is coated on the outer wall surface of the rigid mold 2.
  • the U-shaped long truss pre-forming mold is an important basis for manufacturing the U-shaped long truss wall panel structure, which reduces mold manufacturing costs and indirectly improves the spread of the U-shaped prepreg layer 4 on the skin layer 7
  • the stacking efficiency improves the quality of the corners of the long stringer, ensures the quality and accuracy of the product, and simplifies the process.
  • the rigid mold 2 has a U-shaped structure, which ensures the positioning and longitudinal alignment of the long stringers.
  • the elastic mold 3 has a U-shaped structure, and its thermal expansion ensures the effective transmission of the normal pressure of the fiber layup at the corners of the U-shaped truss and the triangular area, avoids defects such as fiber delamination and pores caused by improper pressure transmission, and ensures The quality of the U-shaped long truss siding structure.
  • the elastic mold 3 adopts the structure of AIRPAD rubber sheet + prepreg layer + AIRPAD rubber sheet. In some embodiments of the present application, the elastic mold 3 can select other structures according to specific needs.
  • the base 1 includes a bottom 11 and a raised portion 12.
  • the raised portion 12 is connected to the bottom 11, and the rigid mold 2 is wrapped on the outer side wall surface of the raised portion 12 and two opposite outer side wall surfaces of the bottom 11 , The width of the protrusion 12 gradually decreases in the direction away from the bottom 11.
  • the width of the raised portion 12 gradually decreases in the direction away from the bottom 11. It can be seen that the raised portion 12 has a trapezoidal structure with a narrow top and a wide bottom, which is convenient for the operator to remove the rigid mold 2 from the base 1.
  • the bottom portion 11 and the protrusion portion 12 may be an integral structure, or may be fixedly connected by welding, bonding or other methods.
  • one of the base 1 and the rigid mold 2 is provided with a card slot, and the other is provided with a card protrusion 21 matching the card slot.
  • the base 1 and the rigid mold 2 are provided with matching connecting parts of the clamping groove and the clamping protrusion 21, which improves the stability of the rigid mold 2 placed on the base 1, not easy to loosen, and improves the quality and accuracy of the product .
  • the connection between the base 1 and the rigid mold 2 is not limited to the mating manner of the card slot and the card protrusion 21, and can be selected according to specific conditions.
  • the corners of the outer side wall of the rigid mold 2 are all arc-shaped.
  • the corners of the outer side wall of the rigid mold 2 are all arc-shaped, which ensures the positioning of the long stringer and the longitudinal alignment.
  • the corners of the inner side wall and the corners of the outer side wall of the elastic mold 3 are both arc-shaped.
  • the corners of the inner side wall and the corners of the outer side wall of the elastic mold 3 are both arc-shaped, which ensures the effective transmission of the applied pressure on the long truss structure during the curing process, and effectively reduces the U-shaped prepreg
  • the stress concentration phenomenon at the corners of the ply 4 avoids the defects such as delamination and pores of the U-shaped prepreg ply 4, and ensures the quality of the U-shaped long truss wall panel structure.
  • the manufacturing method of the U-shaped long truss assembly pre-formed structure in this application uses a U-shaped long truss pre-formed mold, and the method includes the following steps:
  • S4 Distribute multiple U-row long truss preformed structures in a horizontal direction, and place an intermediate interlayer 5 between two adjacent U-shaped long truss preformed structures.
  • the manufacturing method of the U-shaped long truss assembly preformed structure improves the layup efficiency of the U-shaped prepreg layer 4 on the skin layup 7, reduces mold manufacturing costs, and improves the quality of the corners of the long truss , To ensure the quality and accuracy of the product, simplify the process.
  • multiple U-row long truss preformed structures are distributed in the horizontal direction, and an intermediate interlayer 5 is placed between two adjacent U-shaped long truss preformed structures to form a U-row long truss preformed structure group, which is convenient Later positioning, and the axis and straightness of the long stringer can be easily guaranteed, which improves the quality and accuracy of the product.
  • the multi-layer structure in S2 can be AIRPAD rubber sheet + prepreg layer + AIRPAD rubber sheet structure.
  • the rigid mold 2 is mounted on the base 1, and the rigid mold 2 is laid on the elastic mold 3 with a multi-layer structure that is cured and milled to form a U-shaped structure, and then prepreg The material layup is laid on the elastic mold 3, and the U-shaped prepreg layer 4 is formed after vacuum pre-compaction.
  • the base 1, the rigid mold 2, the elastic mold 3 and the U-shaped prepreg layer 4 are formed U-shaped long truss preformed structure, a plurality of U-row long truss preformed structures are distributed in the horizontal direction, and an intermediate interlayer 5 is placed between two adjacent U-shaped long truss preformed structures.
  • the manufacturing method of the U-shaped long truss assembly preformed structure improves the layup efficiency of the U-shaped prepreg layer 4 on the skin layup 7, reduces mold manufacturing costs, improves the quality of the corners of the long truss, and ensures the quality of the product And precision, simplifies the process.
  • the U-shaped prepreg layer 4 is a composite material.
  • Composite materials have the advantages of high rigidity, strong designability and easy integral molding.
  • each intermediate interlayer 5 is fixedly connected to every two U-shaped prepreg layers 4.
  • the intermediate interlayer 5 is used as a medium to connect the two U-shaped prepreg layers 4 together to ensure the connection stability of the two U-shaped prepreg layers 4.
  • each intermediate interlayer 5 of the multiple U-shaped prepreg layers 4 is fixedly connected to every two U-shaped prepreg layers 4, which is beneficial for subsequent operations to connect the multiple U-shaped prepreg layers 4 with other layers. The components are positioned without the need for each U-shaped prepreg layer 4 to be positioned separately, which improves the positioning accuracy and positioning efficiency.
  • the bottom surfaces of the base 1 of a plurality of U-shaped long truss preformed structures are arranged coplanar. It is convenient for later positioning, and the axis and straightness of the long stringer are easily guaranteed, which improves the quality and accuracy of the product.
  • each U-shaped prepreg layer 4 and the intermediate interlayer 5 have a gap, and the gap is filled with filler 6.
  • the filler 6 is filled in the gap between the U-shaped prepreg layer 4 and the intermediate interlayer 5 and fully compacted to effectively transmit the applied pressure, control the defects such as delamination and pores, and ensure the dimensional accuracy And product quality.
  • the filler 6 is a twisted strip. In other embodiments of the present application, the filler 6 is not limited to a twisted strip, and can be selected according to specific needs.
  • the manufacturing method of the U-shaped long truss wall panel structure of the present application includes the following steps:
  • the base 1 in the U-shaped long truss assembly preformed structure is removed, and the skin tooling covered with the skin layer 7 is placed in the horizontal direction.
  • the U-shaped long truss after the base 1 is removed The assembled preformed structure is rotated 180 degrees and placed on the skin layup 7, and the U-shaped prepreg layup 4 and the skin layup 7 are vacuum packaged and then co-cured or co-bonded at a given temperature and pressure. , Remove the skin tooling 8, the rigid mold 2 and the elastic mold 3, and finally obtain the U-shaped long truss wall structure.
  • the manufacturing method of the U-shaped long truss wall structure improves the layup efficiency of the U-shaped prepreg layer 4 on the skin layer 7, reduces mold manufacturing costs, improves the quality of the corners of the long truss, and ensures the quality of the product. Accuracy simplifies the process. Among them, in Q4, the U-shaped prepreg layer 4 and the skin layer 7 are completely bonded, and the bonding area between the two is large, and the stability is strong, which effectively avoids the long stringer degumming and affects the U-shaped stringer The quality of the siding structure.
  • the given temperature range is 25°C-200°C
  • the pressure range is 1-8 standard atmospheres.
  • the given temperature and pressure range can be adjusted according to specific conditions.
  • the rigid mold 2 is installed on the base 1.
  • a multilayer structure is laid on the rigid mold 2 and cured and milled to form an elastic mold 3 with a U-shaped structure.
  • the third step is to lay the prepreg layer on the elastic mold 3. After vacuum pre-compaction, the U-shaped prepreg layer 4 is formed, and the base 1, the rigid mold 2, the elastic mold 3 and the U-shaped prepreg The material layup 4 forms a U-shaped long truss preformed structure.
  • the fourth step is to distribute multiple U-row long truss preformed structures in the horizontal direction, and place an intermediate interlayer 5 between two adjacent U-shaped long truss preformed structures.
  • Each intermediate interlayer 5 is fixedly connected to every two phases.
  • Adjacent U-shaped prepreg layer 4, the bottom surface of the base 1 of multiple U-shaped long truss preformed structures are arranged coplanarly, each U-shaped prepreg layer 4 and the middle interlayer 5 have a gap.
  • the inside is filled with twisted strips to form a U-shaped long stringer assembly preformed structure.
  • the fifth step is to remove the base 1 in the U-shaped long truss assembly pre-formed structure.
  • the skin tooling 8 covered with the skin layer 7 is placed in the horizontal direction.
  • the U-shaped long truss assembly preformed structure after the base 1 is removed is rotated 180 degrees and placed on the skin layer 7.
  • the U-shaped prepreg layer 4 and the skin layer 7 are vacuum packaged and then co-cured or co-bonded under a given temperature and pressure.
  • the ninth step is to remove the skin tooling 8, multiple rigid molds 2 and multiple elastic molds 3.
  • connection unless expressly stipulated and limited otherwise, the terms “connected”, “connected”, “installed”, “fixed” and other terms should be interpreted broadly. For example, it may be a fixed connection or a detachable connection. Or integrated; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication between two components or the interaction between two components.
  • connection may be a fixed connection or a detachable connection. Or integrated; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium, and it can be the internal communication between two components or the interaction between two components.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Health & Medical Sciences (AREA)
  • Toxicology (AREA)
  • Architecture (AREA)
  • Civil Engineering (AREA)
  • Structural Engineering (AREA)
  • Moulding By Coating Moulds (AREA)
  • Moulds, Cores, Or Mandrels (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

一种模具、组装预成型结构的制造方法和壁板结构的制造方法，U型长桁预成型的模具包括基座(1)、刚性模具(2)和弹性模具(3)，刚性模具(2)可拆卸地置于基座(1)上，刚性模具(2)呈U型结构，且包覆在基座(1)的相邻三个外侧壁面上，弹性模具(3)置于刚性模具(2)上且呈U型结构，弹性模具(3)包覆在刚性模具(2)的外侧壁面上。

Description

模具、组装预成型结构的制造方法和壁板结构的制造方法
本申请要求申请日为2019年8月22日、申请号为201910778862.X的中国专利申请的优先权，该申请的全部内容通过引用结合在本申请中。
技术领域
本申请涉及航空制造技术领域，例如涉及一种模具、组装预成型结构的制造方法和壁板结构的制造方法。
背景技术
复合材料以其比刚度高、可设计性强、易于整体成型等优点，在航空航天领域得到广泛应用。在飞行器领域中，复合材料已经用做机翼蒙皮(又名：机翼壁板)、机身、水平尾翼、副翼、垂尾、侧壁板、隔框、翼肋和加强筋等主承力构件。其中，以T型和U型长桁作为加强筋的壁板广泛应用于机身主承力结构。但目前的U型长桁单元铺叠模多为直角型材全钢模，铺叠过程中难以保证垂直部分预浸料与模具面的充分贴合，以及R角区域的充分压实，从而导致外加压力传递不到位，最终出现壁板长桁分层及孔隙缺陷，影响产品质量。T型长桁壁板结构由于长桁底部铺层和蒙皮的胶接面积比较小，长桁容易脱胶从而影响到整个壁板结构的质量。此外，目前的T型和U型长桁壁板结构固化过程中，两侧长桁单元铺层由铺叠工装模取下转移到固化工装后需要重新定位与组合，精度不易保证，工序繁琐且影响长桁轴线定位精准度，容易出现长桁轴线度及直线度不满足要求的情况，同时，其制件的表面质量不佳。
发明内容
本申请提出了一种U型长桁预成型的模具，该模具降低模具制造成本，间接地提高了U型预浸料铺层在蒙皮铺层上的铺叠效率，改进了长桁拐角处的质量，保证了产品的质量和精度，简化了工艺过程。
本申请提出了一种U型长桁组装预成型结构的制造方法，该制造方法提高了U型预浸料铺层在蒙皮铺层上的铺叠效率，降低了模具制造成本，改进了长桁拐角处质量，保证了产品的质量和精度，简化了工艺过程。
本申请提出了一种U型长桁壁板结构的制造方法，该制造方法提高了U型 预浸料铺层在蒙皮铺层上的铺叠效率，降低了模具制造成本，改进了长桁拐角处质量，保证了产品的质量和精度，简化了工艺过程。
一实施例提供一种U型长桁预成型的模具，包括基座、刚性模具和弹性模具；所述刚性模具可拆卸地置于所述基座上，所述刚性模具呈U型结构，且所述刚性模具包覆在所述基座的相邻三个外侧壁面上；所述弹性模具置于所述刚性模具上，所述弹性模具呈U型结构，且所述弹性模具包覆在所述刚性模具的外侧壁面上。
一实施例提供一种U型长桁组装预成型结构的制造方法，采用上述U型长桁预成型的模具，所述方法包括：
将所述刚性模具安装在所述基座上；
在所述刚性模具上铺贴多层结构，经固化、铣切形成为U型结构的所述弹性模具；
将预浸料铺层铺设在所述弹性模具上，经真空预压实后形成U型预浸料铺层，且所述基座、所述刚性模具、所述弹性模具和所述U型预浸料铺层形成U型长桁预成型结构；
将多个所述U行长桁预成型结构沿水平方向分布，相邻两个所述U型长桁预成型结构之间放置中间插层。
一实施例提供一种U型长桁壁板结构的制造方法，采用上述方法制造的U型长桁组装预成型结构，所述方法包括：
将所述U型长桁组装预成型结构中的所述基座拆除；
把铺有蒙皮铺层的蒙皮工装沿水平方向放置；
将拆除所述基座之后的所述U型长桁组装预成型结构整体旋转180度后放置在所述蒙皮铺层上；
将所述U型预浸料铺层和所述蒙皮铺层真空封装后在给定温度、压力下共固化或共胶接成型；
拆除所述蒙皮工装、多个所述刚性模具和多个所述弹性模具。
附图说明
图1是本申请具体实施方式提供的U型长桁预成型的模具的结构示意图；
图2是本申请具体实施方式提供的U型长桁组装预成型结构的结构示意图；
图3是本申请具体实施方式提供的U型长桁壁板结构与刚性模具、弹性模具和蒙皮工装未拆开时的结构示意图；
图4是本申请具体实施方式提供的U型长桁壁板结构的结构示意图；
图5是本申请具体实施方式提供的U型长桁组装预成型结构的制造方法的流程图；
图6是本申请具体实施方式提供的U型长桁壁板结构的制造方法的流程图。
附图标记：
基座-1，底部-11，凸起部-12，刚性模具-2，卡凸-21，弹性模具-3，U型预浸料铺层-4，中间插层-5，填充料-6，蒙皮铺层-7，蒙皮工装-8。
具体实施方式
下面参考图1描述本申请实施例的U型长桁预成型的模具。
本申请中的U型长桁预成型的模具包括基座1、刚性模具2和弹性模具3，刚性模具2可拆卸地置于基座1上，刚性模具2呈U型结构，且刚性模具2包覆在基座1的相邻三个外侧壁面上；弹性模具3置于刚性模具2上，弹性模具3呈U型结构，且弹性模具3包覆在刚性模具2的外侧壁面上。
该U型长桁预成型的模具是制造U型长桁壁板结构的重要基础，其降低了模具制造成本，间接地提高了U型预浸料铺层4在蒙皮铺层7上的铺叠效率，改进了长桁拐角处的质量，保证了产品的质量和精度以及简化了工艺过程。
其中，刚性模具2呈U型结构，确保了长桁的定位及纵向准直度。弹性模具3呈U型结构，其热膨胀性确保了U型长桁拐角处及三角区纤维铺层法向压力的有效传递，避免了压力传递不到位导致的纤维分层及孔隙等缺陷，保证了U型长桁壁板结构的质量。示例性地，弹性模具3采用AIRPAD橡胶片+预浸料铺层+AIRPAD橡胶片的结构形式，在本申请的一些实施例中，弹性模具3可以根据具体需要选择其他的结构形式。
可选地，基座1包括底部11和凸起部12，凸起部12连接在底部11上，刚性模具2包覆在凸起部12的外侧壁面上及底部11相对的两个外侧壁面上，凸起部12的宽度在远离底部11的方向上逐渐减小。
示例性地，凸起部12的宽度在远离底部11的方向逐渐减少，可知凸起部12呈上窄下宽的梯形结构，便于操作人员把刚性模具2从基座1中拆出。另 外，底部11和凸起部12可以是一体成型结构，也可以采用焊接、粘接等其他方式固定连接。
可选地，基座1和刚性模具2的其中一个设有卡槽，另外一个设有与卡槽配合的卡凸21。
示例性地，基座1和刚性模具2上设有卡槽和卡凸21的配合连接件，提高了刚性模具2置于基座1上的稳定性，不易松动，提高了产品的质量和精度。在本申请的其他实施例中，基座1和刚性模具2的连接不限于卡槽和卡凸21的配合方式，可以根据具体情况进行选择。
可选地，刚性模具2的外侧壁拐角处均为圆弧形。示例性地，刚性模具2的外侧壁拐角均为圆弧形，确保了长桁的定位及纵向准直度。
可选地，弹性模具3的内侧壁拐角处及外侧壁拐角处均为圆弧形。本实施例中，弹性模具3的内侧壁拐角处及外侧壁拐角处均为圆弧形，确保了固化过程中外加压力在长桁结构上有效的传递，且有效地减轻了U型预浸料铺层4拐角处出现的应力集中现象，从而避免了U型预浸料铺层4出现分层、孔隙等缺陷，保证了U型长桁壁板结构的质量。
根据图2和图4描述本申请实施例中的U型长桁组装预成型结构的制造方法。
本申请中的U型长桁组装预成型结构的制造方法，该方法采用U型长桁预成型的模具，该方法包括以下步骤：
S1：将刚性模具2安装在基座1上。
S2：在刚性模具2上铺贴多层结构，经固化、铣切后形成为U型结构的弹性模具3。
S3：将预浸料铺层铺设在弹性模具3上，经真空预压实后形成U型预浸料铺层4，且基座1、刚性模具2、弹性模具3和U型预浸料铺层4形成U型长桁预成型结构。
S4：将多个U行长桁预成型结构沿水平方向分布，相邻两个U型长桁预成型结构之间放置中间插层5。
本实施例中，该U型长桁组装预成型结构的制造方法提高了U型预浸料铺层4在蒙皮铺层7上的铺叠效率，降低模具制造成本，改进长桁拐角处质量，保证产品的质量和精度，简化了工艺过程。其中，在S4中，将多个U行长桁预成型结构沿水平方向分布，相邻两个U型长桁预成型结构之间放置中间插层5 形成U行长桁预成型结构组，便于后期的定位，且长桁轴线度和直线度易获得保证，提高了产品的质量和精度。此外，在S2中的多层结构可以为AIRPAD橡胶片+预浸料铺层+AIRPAD橡胶片的结构。
本制造方法相对相关技术的有益效果是：刚性模具2安装在基座1上，在刚性模具2上铺贴多层结构经固化、铣切形成为U型结构的弹性模具3，再将预浸料铺层铺设在弹性模具3上，经真空预压实后形成U型预浸料铺层4，此时，基座1、刚性模具2、弹性模具3和U型预浸料铺层4形成U型长桁预成型结构，将多个U行长桁预成型结构沿水平方向分布，相邻两个U型长桁预成型结构之间放置中间插层5。该U型长桁组装预成型结构的制造方法提高了U型预浸料铺层4在蒙皮铺层7上的铺叠效率，降低模具制造成本，改进长桁拐角处质量，保证产品的质量和精度，简化了工艺过程。
有利地，U型预浸料铺层4为复合材料。复合材料具有刚度高、可设计性强、易于整体成型的优点。
可选地，在S4中，每个中间插层5固定连接每两个U型预浸料铺层4。示例性地，由于U型预浸料铺层4固化后，相邻的两个U型预浸料铺层4如果直接粘接会使得两个U型预浸料铺层4连接不稳定。而在本申请中，采用中间插层5作为媒介将两个U型预浸料铺层4连接在一起，保证了两个U型预浸料铺层4的连接稳定性。并且，多个U型预浸料铺层4中每个中间插层5固定连接每两个U型预浸料铺层4，有利于后续操作将多个U型预浸料铺层4与其他部件进行定位，不必每个U型预浸料铺层4单独定位，提升了定位精度和定位效率。
可选地，多个U型长桁预成型结构的基座1的底面共面设置。其便于后期的定位，且长桁轴线度和直线度易获得保证，提高了产品的质量和精度。
可选地，每个U型预浸料铺层4与中间插层5均有间隙，间隙内填充有填充料6。本实施中，在U型预浸料铺层4与中间插层5的间隙内填充填充料6，并充分压实，有效地传递外加压力，控制了分层、孔隙等缺陷，保证了尺寸精度和产品质量。一般情况下，填充料6为捻子条，在本申请的其他实施例中，填充料6不限于捻子条，可以根据具体需要进行选择。
根据图3、图4和图6描述本申请实施例中的U型长桁壁板结构的制造方法。
本申请的U型长桁壁板结构的制造方法，该方法包括以下步骤：
Q1：将U型长桁组装预成型结构中的基座1拆除。
Q2：把铺有蒙皮铺层7的蒙皮工装8沿水平方向放置。
Q3：将拆除基座1之后的U型长桁组装预成型结构整体旋转180度后放置在蒙皮铺层7上。
Q4：将U型预浸料铺层4和蒙皮铺层7真空封装后在给定温度、压力下共固化或共胶接成型。
Q5：拆除蒙皮工装8、多个刚性模具2和多个弹性模具3。
本实施例中，将U型长桁组装预成型结构中的基座1拆除，把铺有蒙皮铺层7的蒙皮工装在水平方向上放置，将拆除基座1之后的U型长桁组装预成型结构整体旋转180度后放置在蒙皮铺层7上，将U型预浸料铺层4和蒙皮铺层7真空封装后在给定温度、压力下共固化或共胶接成型，拆除蒙皮工装8、刚性模具2和弹性模具3，最后获得U型长桁壁板结构。该U型长桁壁板结构的制造方法提高了U型预浸料铺层4在蒙皮铺层7上的铺叠效率，降低模具制造成本，改进长桁拐角处质量，保证产品的质量和精度，简化了工艺过程。其中，在Q4中，U型预浸料铺层4与蒙皮铺层7完全贴合，两者的胶接面积较大，稳定性强，有效地避免了长桁脱胶从而影响U型长桁壁板结构的质量。
示例性地，一般情况下，给定温度范围为25℃-200℃，压力范围为1-8个标准大气压。在本申请的其他实施例中，给定的温度和压力范围可以根据具体情况进行调整。
下面描述本申请的一个具体实施例的U型长桁壁板结构的制造方法。
第一步，将刚性模具2安装在基座1上。
第二步，在刚性模具2上铺贴多层结构，经固化、铣切后形成为U型结构的弹性模具3。
第三步，将预浸料铺层铺设在弹性模具3上，经真空预压实后形成U型预浸料铺层4，且基座1、刚性模具2、弹性模具3和U型预浸料铺层4形成U型长桁预成型结构。
第四步，将多个U行长桁预成型结构沿水平方向分布，相邻两个U型长桁预成型结构之间放置中间插层5，每个中间插层5固定连接每两个相邻的U型预浸料铺层4，多个U型长桁预成型结构的基座1的底面共面设置，每个U型预浸料铺层4与中间插层5均有间隙，间隙内填充有捻子条，从而形成U型长桁组装预成型结构。
第五步，将U型长桁组装预成型结构中的基座1拆除。
第六步，把铺有蒙皮铺层7的蒙皮工装8沿水平方向放置。
第七步，将拆除基座1之后的U型长桁组装预成型结构整体旋转180度后放置在蒙皮铺层7上。
第八步，将U型预浸料铺层4和蒙皮铺层7真空封装后在给定温度、压力下共固化或共胶接成型。
第九步，拆除蒙皮工装8、多个刚性模具2和多个弹性模具3。
在本说明书的描述中，参考术语“有些实施例”、“其他实施例”等的描述意指结合该实施例或示例描述的具体特征、结构、材料或者特点包含于本申请的至少一个实施例或示例中。在本说明书中，对上述术语的示意性表述不一定指的是相同的实施例或示例。而且，描述的具体特征、结构、材料或者特点可以在任何的一个或多个实施例或示例中以合适的方式结合。
此外，需要理解的是，术语“上”、“下”、“内”、“外”、“竖直”、“水平”等指示的方位或者位置关系为基于附图所示的方位或位置关系，仅是为了便于描述本申请和简化描述，而不是指示或暗示所指的装置或元件必须具有特定的方位、以特定的方位构造和操作，因此不能理解为对本申请的限制。
在本申请中，除非另有明确的规定和限定，“相连”、“连接”、“安装”、“固定”等术语应做广义理解，例如，可以是固定连接，也可以是可拆卸连接，或成一体；可以是机械连接，也可以是电连接；可以是直接连接，也可以通过中间媒介间接连接，可以是两个元件内部的连通或两个元件的相互作用关系。对于本领域的普通技术人员而言，可以根据具体情况理解上述属于在本申请中的具体含义。

Claims (10)

  1. 一种U型长桁预成型的模具，包括：
    基座(1)；
    刚性模具(2)，所述刚性模具(2)可拆卸地置于所述基座(1)上，所述刚性模具(2)呈U型结构，且所述刚性模具(2)包覆在所述基座(1)的相邻三个外侧壁面上；
    弹性模具(3)，所述弹性模具(3)置于所述刚性模具(2)上，所述弹性模具(3)呈U型结构，且所述弹性模具(3)包覆在所述刚性模具(2)的外侧壁面上。
  2. 如权利要求1所述的U型长桁预成型的模具，其中，所述基座(1)包括底部(11)和凸起部(12)，所述凸起部(12)连接在所述底部(11)上，所述刚性模具(2)包覆在所述凸起部(12)的外侧壁面上及所述底部(11)相对的两个外侧壁面上，所述凸起部(12)的宽度在远离所述底部(11)的方向上逐渐减小。
  3. 如权利要求1所述的U型长桁预成型的模具，其中，所述基座(1)和所述刚性模具(2)的其中一个设有卡槽，另外一个设有与所述卡槽配合的卡凸(21)。
  4. 如权利要求1所述的U型长桁预成型的模具，其中，所述刚性模具(2)的外侧壁拐角处为圆弧形。
  5. 如权利要求1所述的U型长桁预成型的模具，其中，所述弹性模具(3)的内侧壁拐角处及外侧壁拐角处为圆弧形。
  6. 一种U型长桁组装预成型结构的制造方法，采用如权利要求1-5任一项所述的U型长桁预成型的模具，所述方法包括：
    将所述刚性模具(2)安装在所述基座(1)上；
    在所述刚性模具(2)上铺贴多层结构，经固化、铣切后形成为U型结构的所述弹性模具(3)；
    将预浸料铺层铺设在所述弹性模具(3)上，经真空预压实后形成U型预浸料铺层(4)，且所述基座(1)、所述刚性模具(2)、所述弹性模具(3)和所述U型预浸料铺层(4)形成U型长桁预成型结构；
    将多个所述U型长桁预成型结构沿水平方向分布，相邻两个所述U型长桁预成型结构之间放置中间插层(5)。
  7. 如权利要求6所述的U型长桁组装预成型结构的制造方法，其中，每个 所述中间插层(5)设置为固定连接每两个相邻的所述U型预浸料铺层(4)。
  8. 如权利要求6所述的U型长桁组装预成型结构的制造方法，其中，所述多个U型长桁预成型结构的所述基座(1)的底面共面设置。
  9. 如权利要求6所述的U型长桁组装预成型结构的制造方法，其中，每个所述U型预浸料铺层(4)与所述中间插层(5)之间的间隙内填充有填充料(6)。
  10. 一种U型长桁壁板结构的制造方法，采用如权利要求6所述的方法制造的U型长桁组装预成型结构，所述方法包括：
    将所述U型长桁组装预成型结构中的所述基座(1)拆除；
    把铺有蒙皮铺层(7)的蒙皮工装(8)沿水平方向放置；
    将拆除所述基座(1)之后的所述U型长桁组装预成型结构整体旋转180度后放置在所述蒙皮铺层(7)上；
    将所述U型预浸料铺层(4)和所述蒙皮铺层(7)真空封装后在给定温度、压力下共固化或共胶接成型；
    拆除所述蒙皮工装(8)、多个所述刚性模具(2)和多个所述弹性模具(3)。
PCT/CN2020/110183 2019-08-22 2020-08-20 模具、组装预成型结构的制造方法和壁板结构的制造方法 WO2021032150A1 (zh)

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Publication number Priority date Publication date Assignee Title
CN110480884B (zh) * 2019-08-22 2022-06-24 中国商用飞机有限责任公司北京民用飞机技术研究中心 模具、组装预成型结构的制造方法和壁板结构的制造方法
CN111016003B (zh) * 2019-12-13 2021-09-07 西安鑫垚陶瓷复合材料有限公司 定型工装及使用定型工装的C/SiC复合材料结构件成型方法
CN110978564B (zh) * 2019-12-13 2021-11-02 中国航空工业集团公司基础技术研究院 一种u形单元加筋壁板的整体成型方法
CN111347694B (zh) * 2020-03-18 2021-08-31 广联航空工业股份有限公司 一种带立筋复合材料加筋壁板热压罐整体成型方法
CN112356462B (zh) * 2020-10-16 2023-03-24 中国商用飞机有限责任公司北京民用飞机技术研究中心 复合材料u型长桁加筋壁板结构的整体成型工装及工艺

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2333832C2 (ru) * 2006-09-15 2008-09-20 ФГУП Кумертауское авиационное производственное предприятие Способ изготовления многоканальных лопастей из композиционных материалов
CN103042700A (zh) * 2012-12-27 2013-04-17 中国科学院工程热物理研究所 一种分段叶片一体化成型方法及装置
CN104210670A (zh) * 2013-05-30 2014-12-17 空中客车营运有限公司 用于固化复合材料的工件的混合式工具
CN107415280A (zh) * 2017-08-22 2017-12-01 中国商用飞机有限责任公司北京民用飞机技术研究中心 用于t型长桁的预成型和/或其与壁板定位的模具和方法
CN110480884A (zh) * 2019-08-22 2019-11-22 中国商用飞机有限责任公司北京民用飞机技术研究中心 模具、组装预成型结构的制造方法和壁板结构的制造方法

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5817269A (en) * 1996-10-25 1998-10-06 The Boeing Company Composite fabrication method and tooling to improve part consolidation
FR2863197B1 (fr) * 2003-12-04 2006-03-03 Airbus France Procede de mise en place des elements d'un panneau auto-raidi en composite preimpregne
CN107253334B (zh) * 2017-04-28 2023-03-21 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种成型复合材料t形长桁加筋壁板的模具及工艺
CN207327652U (zh) * 2017-08-22 2018-05-08 中国商用飞机有限责任公司北京民用飞机技术研究中心 用于t型长桁的预成型和/或其与壁板的组装定位的模具
CN108248071B (zh) * 2018-01-15 2020-07-31 成都市泰格尔航天航空科技有限公司 口形梁的制造方法
CN109203492A (zh) * 2018-09-04 2019-01-15 沈阳飞机工业（集团）有限公司 一种大尺寸加筋壁板成型方法
CN209063598U (zh) * 2018-11-14 2019-07-05 中国商用飞机有限责任公司 一种t型长桁壁板结构的成型模具

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2333832C2 (ru) * 2006-09-15 2008-09-20 ФГУП Кумертауское авиационное производственное предприятие Способ изготовления многоканальных лопастей из композиционных материалов
CN103042700A (zh) * 2012-12-27 2013-04-17 中国科学院工程热物理研究所 一种分段叶片一体化成型方法及装置
CN104210670A (zh) * 2013-05-30 2014-12-17 空中客车营运有限公司 用于固化复合材料的工件的混合式工具
CN107415280A (zh) * 2017-08-22 2017-12-01 中国商用飞机有限责任公司北京民用飞机技术研究中心 用于t型长桁的预成型和/或其与壁板定位的模具和方法
CN110480884A (zh) * 2019-08-22 2019-11-22 中国商用飞机有限责任公司北京民用飞机技术研究中心 模具、组装预成型结构的制造方法和壁板结构的制造方法

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP4019220A4

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