CN109435275B - Integral manufacturing method of large-size space double-S-bend composite material component - Google Patents

Integral manufacturing method of large-size space double-S-bend composite material component Download PDF

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Publication number
CN109435275B
CN109435275B CN201811194040.9A CN201811194040A CN109435275B CN 109435275 B CN109435275 B CN 109435275B CN 201811194040 A CN201811194040 A CN 201811194040A CN 109435275 B CN109435275 B CN 109435275B
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composite material
die
thin
male
mold body
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CN109435275A (en
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靳通
匡海华
孙广先
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AVIC Research Institute Special Structures Aeronautical Composites
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AVIC Research Institute Special Structures Aeronautical Composites
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/34—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • 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
    • 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
    • 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
    • B29C33/56—Coatings, e.g. enameled or galvanised; Releasing, lubricating or separating agents
    • B29C33/60—Releasing, lubricating or separating agents
    • 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
    • B29C33/56—Coatings, e.g. enameled or galvanised; Releasing, lubricating or separating agents
    • B29C33/68—Release sheets
    • 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

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Mounting, Exchange, And Manufacturing Of Dies (AREA)
  • Moulds For Moulding Plastics Or The Like (AREA)

Abstract

The invention discloses an integral manufacturing method of a large-size spatial double-S-bend composite material member, which provides a composite forming die in a structural form of a low-cost female die and a thin-shell composite material male die, integrates the functions of forming surface processing, heat distribution test, profile finish machining degree detection and the like to form a structural function integrated die, solves the problems of high requirement on the dimensional precision of the composite material member, high requirement on the roughness grade of the inner surface, heat distribution test of the forming die and the like, and provides a forming die using the thin-shell composite material male die as the composite material member; the composite material member is in a spatial double-S-bend shape, has large curvature change, large height dimension and no die drawing angle, solves the problem of difficult integral demolding of the blank caused by the structural characteristics, considers overcoming the deformation problem in the demolding process, can realize the layer-by-layer peeling removal of the die on the member blank after the surface treatment of the thin-shell composite material male die, has no external force in the demolding process, and has no impact damage to the member blank.

Description

Integral manufacturing method of large-size space double-S-bend composite material component
Technical Field
The invention belongs to the technical field of civil aircraft composite material component manufacturing processes, and particularly relates to a method for integrally manufacturing a large-size space double-S-bend composite material component.
Background
The composite material structural member has the advantages of light weight, high strength and rigidity, good forming manufacturability and the like, and is more and more widely applied to the field of civil aircrafts, in particular to a large-scale composite material structural member.
The large-size space double-S-bend composite material component is an off-board channel of a C919 large-scale passenger plane, belongs to a seaworthy part, and the requirement of a forming die heat distribution test needs to meet the requirement of civil aircraft process specifications; the appearance is in a space double S-bend shape, the curvature change is large, the height size is large, and the demoulding is difficult by adopting the traditional manufacturing method; the thin-shell cavity component has high requirements on the precision of the inner and outer dimensions and high requirements on the design and manufacture of process equipment.
The domestic research on the integral manufacture of composite material members is mainly applied to the aspects of the manufacture of airplane air inlet channels with small size and gentle curvature change and the like, has no airworthiness manufacture requirement, and can be solved by the traditional manufacturing process methods such as a thin-wall metal split type male die method, a water-soluble die method and the like.
Disclosure of Invention
Object of the Invention
The invention provides a method for integrally manufacturing a large-size spatial double-S-bend composite material member, which solves the problems of difficult integral forming and manufacturing, uniform heat distribution of a forming die, high manufacturing cost of the forming die, long development period and the like caused by large height and size of a product, spatial double-S-bend and large curvature change in the forming and manufacturing of the composite material member.
Technical solution of the invention
In order to achieve the purpose, the invention adopts the following technical scheme:
the integral manufacturing method of the large-size space double-S-shaped bent composite material member is characterized by comprising the following steps of:
step 1: selecting a low-cost material as a female die material, vacuumizing and compacting a female die blank in an oven, then roughly and finely machining the outer molded surface of the female die on a numerical control machine tool to form a molding surface of the inner molded surface of the male die of the thin-shell composite material, and detecting the outer molded surface of the female die;
step 2: forming a thin-shell composite male die on the outer molded surface of the female die, after the solidification is finished, carrying out numerical control machining on the outer molded surface of the thin-shell composite male die to form a molded surface of the inner molded surface of the composite member, and detecting the outer molded surface of the thin-shell composite male die;
and step 3: disassembling the female die, reserving the thin-shell composite male die, and performing precision detection on the outer profile of the male die;
and 4, step 4: carrying out a heat distribution test on the thin-shell composite male die, and taking the male die as a forming die of a composite material component after the test is passed;
and 5: accurately paving a composite material member blank on the outer surface of the thin-shell composite material male die, and accurately processing the boundary of the composite material member blank on a numerical control machine after the composite material member blank is formed and solidified;
step 6: stripping and removing the thin-shell composite male die layer by layer to form a blank after stripping, and forming a composite member after cutting and spraying;
and 7: and carrying out precision detection on the inner molded surface of the composite material member, and carrying out nondestructive detection.
Preferably, between steps 1 and 2: and (3) carrying out surface treatment on the outer surface of the female die, and uniformly coating a demolding layer on the outer surface to realize the isolation from the inner surface of the thin-shell composite material male die.
Preferably, between steps 4 and 5: and (3) carrying out surface treatment on the outer surface of the thin-shell composite male die, and paving an isolating film to form isolation from the inner surface of the composite member blank during forming.
Preferably, a three-coordinate measuring machine is used for profile testing in steps 1, 2, 3, 7.
Preferably, the female die comprises a female die body, the female die body is double-S-shaped, and the area of the end face of one end is larger than that of the end face of the other end; the end face of the big end of the female die body is detachably connected with a supporting plate.
Preferably, the thin-shell composite material male die comprises a male die body, the male die body is of a double-S-shaped hollow structure with two open ends, the open area of one end is larger than that of the other end, a supporting plate is detachably connected to the large-end face of the male die body, and a reinforcing frame is arranged on one side of the large-end face.
Preferably, the peripheral surface of the supporting plate, the top surface and the peripheral surface of the reinforcing frame are provided with a plurality of hanging rings.
Preferably, the supporting plate is square, and positioning blocks are further arranged at four corners of the top surface of the supporting plate.
Preferably, the master mold body is made of a wood material.
Preferably, in the step 5, when the composite material member is cured on the thin-shell composite material male mold, the male mold body is placed horizontally, the small end of the male mold body is provided with a small end adjusting frame, the large end of the male mold body is provided with a large end adjusting frame, the upper ends of the small end adjusting frame and the large end adjusting frame are arranged on the inner top surface of the male mold body, so that the small end port of the male mold body faces the air flow direction in the hot-pressing tank, and the cross section of the port is perpendicular to the horizontal plane. Because the inner cavity of the male die is hollow and communicated, the horizontal die placing mode can ensure smooth airflow and uniform heating of the die when the composite material member blank is cured.
THE ADVANTAGES OF THE PRESENT INVENTION
The invention has the advantages that:
1) the method has wide application range and can be suitable for the integral manufacture of various large-size and large-curvature-change composite material members.
2) The mold has low design and manufacturing cost and short development period.
3) The product demoulding process has no external force, and the deformation of the product in the demoulding process is reduced.
Drawings
FIG. 1 is a flow chart of the overall manufacturing method of the large-size spatial double S-bend composite material member of the present invention.
FIG. 2 is a front view of the master model.
FIG. 3 is a top view of the master mold.
FIG. 4 is a three-dimensional structural view of a master mold.
Figure 5 is a front view of a thin shell composite male mold.
Figure 6 is a top view of a thin shell composite male mold.
FIG. 7 is a three-dimensional structural view of a thin shell composite male mold.
Figure 8 is a front view of a composite member blank as it is being cured on a thin shell composite male mold.
Figure 9 is a three-dimensional view of a composite member blank as it is being cured on a thin shell composite male mold.
In the figure: 1-anti-drop screw; 2-a female die body; 3-a support plate; 4-hoisting rings; 5-positioning a block; 6-a positive mold body; 7-small end adjusting rack; 8-large end adjusting frame; 9-reinforcing frame.
Detailed Description
The detailed description of the embodiments of the present invention is provided in conjunction with the summary of the invention and the accompanying drawings.
The integral manufacturing method of the large-size space double-S-shaped bent composite material member comprises the following steps:
step 1: selecting a low-cost material as a female die material, vacuumizing and compacting a female die blank in an oven, then roughly and finely machining the outer molded surface of the female die on a numerical control machine tool to form a molded surface of the inner molded surface of the male die of the thin-shell composite material, and detecting the outer molded surface of the female die by using a three-coordinate measuring machine;
step 2: forming a thin-shell composite male die on the outer molding surface of the female die, after the solidification is finished, carrying out numerical control machining on the outer molding surface of the thin-shell composite male die to form a molding surface of the inner molding surface of the composite member, and detecting the outer molding surface of the thin-shell composite male die by using a three-coordinate measuring machine;
and step 3: disassembling the female die, reserving the thin-shell composite male die, and performing precision detection on the outer molded surface of the male die by using a three-coordinate measuring machine;
and 4, step 4: carrying out a heat distribution test on the thin-shell composite male die, and taking the male die as a forming die of a composite material component after the test is passed;
and 5: accurately paving a composite material member blank on the outer surface of the thin-shell composite material male die, and accurately processing the boundary of the composite material member blank on a numerical control machine after the composite material member blank is formed and solidified;
step 6: stripping and removing the thin-shell composite male die layer by layer to form a blank after stripping, and forming a composite member after cutting and spraying;
and 7: and (3) carrying out precision detection on the inner molded surface of the composite material member by using a three-coordinate measuring machine, and carrying out nondestructive detection.
Between steps 1 and 2: and (3) carrying out surface treatment on the outer surface of the female die, and uniformly coating a demolding layer on the outer surface to realize the isolation from the inner surface of the thin-shell composite material male die.
Between steps 4 and 5: and (3) carrying out surface treatment on the outer surface of the thin-shell composite male die, and paving an isolating film to form isolation from the inner surface of the composite member blank during forming.
In order to solve the problems of high requirement on the dimensional precision of a composite material member, high requirement on the roughness grade of the inner surface, heat distribution test of a forming die and the like, the forming die using a thin-shell composite material male die as the composite material member is provided; the composite material member is in a spatial double-S-bend shape, has large curvature change, large height dimension and no die drawing angle, solves the problem of difficult overall die removal of a blank caused by the structural characteristics, considers overcoming the deformation problem in the die removal process, can realize the layer-by-layer peeling removal of the die on the member blank after the surface treatment of the thin-shell composite material male die, has no external force in the die removal process, and has no impact damage to the member blank; in order to realize the molding manufacture of the thin-shell composite male die, a low-cost female die is selected as a molding die. Based on the analysis, the composite forming die with the structural form of the low-cost female die and the thin-shell composite male die is provided.
The female die comprises a female die body 2, the female die body 2 is of a double-S-shaped solid structure, and the area of the end face of one end is larger than that of the end face of the other end; the large end face of the female die body 2 is detachably connected with a supporting plate 3 with a plate-shaped structure. The small end of the female die body 2 is provided with a plurality of anti-drop screws 1.
The thin-shell composite material male die comprises a male die body 6, wherein the male die body 6 is of a double-S-shaped hollow structure with two open ends, the outer surface of the male die body 6 is matched with the inner surface structure of a composite material member, the open area of one end is larger than that of the other end, a supporting plate 3 of a plate-shaped structure can be detachably connected with the large end surface of the male die body 6, and a reinforcing frame 9 is arranged on one side of the large end surface. The small end of the male die body 6 is provided with a plurality of anti-drop screws 1.
The peripheral surface of the supporting plate 3, the top surface and the peripheral surface of the reinforcing frame 9 are provided with a plurality of hanging rings 4.
The supporting plate 3 is square, and positioning blocks 5 are further arranged at four corners of the top surface of the supporting plate 3.
The master model body 2 is made of wood material.
And 5, when the composite material member is cured on the thin-shell composite material male die, horizontally placing the male die body 6, arranging a small end adjusting frame 7 at the small end of the male die body 6, arranging a large end adjusting frame 8 at the large end of the male die body 6, and arranging the upper ends of the small end adjusting frame 7 and the large end adjusting frame 8 on the inner top surface of the male die body 6 so that the small end port of the male die body faces to the air flow direction in the hot-pressing tank, wherein the cross section of the port is vertical to the horizontal plane.
The dimensions of the composite material member manufactured in this example were: the height is 1600mm, and the size of the inner cavity is 800mm multiplied by 800 mm.

Claims (10)

1. The integral manufacturing method of the large-size space double-S-shaped bent composite material member is characterized by comprising the following steps of:
step 1: selecting a low-cost material as a female die material, vacuumizing and compacting a female die blank in an oven, then roughly and finely machining the outer molded surface of the female die on a numerical control machine tool to form a molding surface of the inner molded surface of the male die of the thin-shell composite material, and detecting the outer molded surface of the female die;
step 2: forming a thin-shell composite male die on the outer molded surface of the female die, after the solidification is finished, carrying out numerical control machining on the outer molded surface of the thin-shell composite male die to form a molded surface of the inner molded surface of the composite member, and detecting the outer molded surface of the thin-shell composite male die;
and step 3: disassembling the female die, reserving the thin-shell composite male die, and performing precision detection on the outer profile of the male die;
and 4, step 4: carrying out a heat distribution test on the thin-shell composite male die, and taking the male die as a forming die of a composite material component after the test is passed;
and 5: accurately paving a composite material member blank on the outer surface of the thin-shell composite material male die, and accurately processing the boundary of the composite material member blank on a numerical control machine after the composite material member blank is formed and solidified;
step 6: stripping and removing the thin-shell composite male die layer by layer to form a blank after stripping, and forming a composite member after cutting and spraying;
and 7: and carrying out precision detection on the inner molded surface of the composite material member, and carrying out nondestructive detection.
2. The method for integrally manufacturing a large-sized spatial double S-bend composite material member according to claim 1, wherein between steps 1 and 2: and (3) carrying out surface treatment on the outer surface of the female die, and uniformly coating a demolding layer on the outer surface to realize the isolation from the inner surface of the thin-shell composite material male die.
3. The method for integrally manufacturing a large-sized spatial double S-bend composite material member according to claim 1, wherein between steps 4 and 5: and (3) carrying out surface treatment on the outer surface of the thin-shell composite male die, and paving an isolating film to form isolation from the inner surface of the composite member blank during forming.
4. The method for integrally manufacturing a large-size spatial double S-bend composite material member according to claim 1, wherein the step 1, 2, 3, 7 is performed by using a three-coordinate measuring machine for profile inspection.
5. The method of integrally manufacturing a large-sized spatial double-S-bend composite material member as recited in claim 1, wherein the female mold comprises a female mold body, the female mold body is double-S-shaped and has an end surface area at one end larger than an end surface area at the other end; the end face of the big end of the female die body is detachably connected with a supporting plate.
6. The method for integrally manufacturing a large-size spatial double-S-bend composite material member as claimed in claim 5, wherein the thin-shell composite material male mold comprises a male mold body, the male mold body is a double-S-shaped hollow structure with two open ends, the open area of one end is larger than that of the other end, a support plate is detachably connected to the large end face of the male mold body, and a reinforcing frame is arranged on one side of the large end face.
7. The method as claimed in claim 6, wherein the reinforcing frame has a plurality of rings formed on the outer peripheral surface of the supporting plate of the male mold body and the female mold body.
8. The method for integrally manufacturing a large-sized spatial double-S-bend composite material member as recited in claim 6, wherein the supporting plates of the female mold body and the male mold body are square, and positioning blocks are further disposed at four corners of the top surface of the supporting plate.
9. The method of integrally manufacturing a large-sized spatial double S-bend composite material member as recited in claim 1, wherein the master mold body is made of a wooden material.
10. The method for integrally manufacturing a large-size spatial double-S-shaped composite material member according to claim 6, wherein in the step 5, when the composite material member blank is cured on the thin-shell composite material male mold, the male mold body is horizontally placed, the small end adjusting frame is arranged at the small end of the male mold body, the large end adjusting frame is arranged at the large end of the male mold body, the upper ends of the small end adjusting frame and the large end adjusting frame are arranged on the inner top surface of the male mold body, so that the small end port of the male mold body faces to the air flow direction in the hot-pressing tank, and the cross section of the port is perpendicular to the horizontal plane.
CN201811194040.9A 2018-10-12 2018-10-12 Integral manufacturing method of large-size space double-S-bend composite material component Active CN109435275B (en)

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US5773108A (en) * 1996-06-14 1998-06-30 Lockheed Martin Corporation Self-coiling composite band
CN201525132U (en) * 2009-09-08 2010-07-14 国营江北机械厂 Detachable core die
CN202846881U (en) * 2012-08-29 2013-04-03 天津鹏翎胶管股份有限公司 Combined core rod of cloth-winded hose for automobile
US9981421B2 (en) * 2014-07-16 2018-05-29 The Boeing Company Adaptive composite structure using shape memory alloys
CN106553357A (en) * 2016-11-09 2017-04-05 江苏恒神股份有限公司 Hollow multi-cavity abnormal shape surface composite material complex structural member integral forming technique
CN106393743A (en) * 2016-11-30 2017-02-15 江西洪都航空工业集团有限责任公司 Composite material intake way forming mold
CN108527732B (en) * 2018-03-14 2019-10-11 天津爱思达航天科技有限公司 A kind of composite material mould and its manufacturing method

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