CN105082575B - 制造用于飞行器结构的由复合材料制成的部件的方法 - Google Patents

制造用于飞行器结构的由复合材料制成的部件的方法 Download PDF

Info

Publication number
CN105082575B
CN105082575B CN201510232363.2A CN201510232363A CN105082575B CN 105082575 B CN105082575 B CN 105082575B CN 201510232363 A CN201510232363 A CN 201510232363A CN 105082575 B CN105082575 B CN 105082575B
Authority
CN
China
Prior art keywords
preform
reinforcing
composite material
reinforced
resin
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.)
Active
Application number
CN201510232363.2A
Other languages
English (en)
Other versions
CN105082575A (zh
Inventor
丹尼斯·苏拉
杰罗姆·科尔马格罗
马蒂厄·普莱
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
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 Airbus Operations SAS filed Critical Airbus Operations SAS
Publication of CN105082575A publication Critical patent/CN105082575A/zh
Application granted granted Critical
Publication of CN105082575B publication Critical patent/CN105082575B/zh
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Images

Classifications

    • 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
    • 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
    • B29C70/50—Shaping or impregnating by compression not applied for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
    • B29C70/52—Pultrusion, i.e. forming and compressing by continuously pulling through a die
    • 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
    • B29C70/50—Shaping or impregnating by compression not applied for producing articles of indefinite length, e.g. prepregs, sheet moulding compounds [SMC] or cross moulding compounds [XMC]
    • B29C70/52—Pultrusion, i.e. forming and compressing by continuously pulling through a die
    • B29C70/523—Pultrusion, i.e. forming and compressing by continuously pulling through a die and impregnating the reinforcement in the die
    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/84—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined
    • 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
    • B29D99/0046—Producing 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
    • B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
    • B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
    • B29C35/0277—Apparatus with continuous transport of the material to be cured
    • 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
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/53—Joining single elements to tubular articles, hollow articles or bars
    • B29C66/532—Joining single elements to the wall of tubular articles, hollow articles or bars
    • B29C66/5324—Joining single elements to the wall of tubular articles, hollow articles or bars said single elements being substantially annular, i.e. of finite length
    • 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
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/53—Joining single elements to tubular articles, hollow articles or bars
    • B29C66/534—Joining single elements to open ends of tubular or hollow articles or to the ends of bars
    • B29C66/5344—Joining single elements to open ends of tubular or hollow articles or to the ends of bars said single elements being substantially annular, i.e. of finite length, e.g. joining flanges to tube ends
    • 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
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/71—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the composition of the plastics material of the parts to be joined
    • 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
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • 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
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7212—Fibre-reinforced materials characterised by the composition of the fibres
    • 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
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B29C66/7214—Fibre-reinforced materials characterised by the length of the fibres
    • B29C66/72141—Fibres of continuous length
    • 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
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/737—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined
    • B29C66/7375—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured
    • B29C66/73753—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being partially cured, i.e. partially cross-linked, partially vulcanized
    • B29C66/73754—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the state of the material of the parts to be joined uncured, partially cured or fully cured the to-be-joined area of at least one of the parts to be joined being partially cured, i.e. partially cross-linked, partially vulcanized the to-be-joined areas of both parts to be joined being partially cured
    • 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
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/73—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/739—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset
    • B29C66/7394—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoset
    • B29C66/73941—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the intensive physical properties of the material of the parts to be joined, by the optical properties of the material of the parts to be joined, by the extensive physical properties of the parts to be joined, by the state of the material of the parts to be joined or by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of the parts to be joined being a thermoplastic or a thermoset characterised by the material of at least one of the parts being a thermoset characterised by the materials of both parts being thermosets
    • 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
    • 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
    • B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
    • B29C70/462—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
    • 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
    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • 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
    • B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
    • B29C70/86—Incorporated in coherent impregnated reinforcing layers, e.g. by winding
    • B29C70/865—Incorporated in coherent impregnated reinforcing layers, e.g. by winding completely encapsulated
    • 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
    • B29L2031/06—Rods, e.g. connecting rods, rails, stakes
    • 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
    • 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
    • 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
    • B29L2031/3085—Wings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16C—SHAFTS; FLEXIBLE SHAFTS; ELEMENTS OR CRANKSHAFT MECHANISMS; ROTARY BODIES OTHER THAN GEARING ELEMENTS; BEARINGS
    • F16C7/00—Connecting-rods or like links pivoted at both ends; Construction of connecting-rod heads
    • F16C7/02—Constructions of connecting-rods with constant length
    • F16C7/026—Constructions of connecting-rods with constant length made of fibre reinforced resin
    • 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)
  • Moulding By Coating Moulds (AREA)

Abstract

本发明提供一种制造用于飞行器结构的由复合材料制成的部件的方法，用于飞行器的结构元件的制造需要使用复杂且昂贵的方法，特别是在由复合材料制成的长形整体形状的并且可变厚度或横截面的部件的情况下。本发明建议通过如下方法克服这个问题：该方法允许结构部件(70)由预成形件(64)和一个或更多个加强元件(76、78)制造，该预成形件(64)通过拉挤成型获得、由简单形状的复合材料制成，所述一个或更多个加强元件(76、78)由复合材料制成并且通过与预成形件共固化而紧固至该预成形件的待加强的区域(74)。

Description

制造用于飞行器结构的由复合材料制成的部件的方法
技术领域
本发明涉及用于制造意在结合至飞行器的结构中的由复合材料制成的部件的方法。
背景技术
图1和图2分别图示了飞行器机身10的部段和飞行器中央翼盒12的一部分。
如图1所示，机身10包括多个长形整体形状的结构部件。这些部件包括例如机身的纵向加劲件14、地板横向构件16、地板轨道18以及地板支承支柱20，该纵向加劲件14还被称为“纵梁”，该地板支承支柱20还被称为将地板横向构件16连接至机身的周向框架22的“立柱”。这些各种部件采用大梁的整体形状，该大梁的整体形状的横截面为大致C形、I形、L形、Z形或欧米茄形形状的。
如图2所示，中央翼盒12包括结构联杆24，所述结构联杆24各自包括管状中央部分26和分别形成附接轭部的端部28。
这些各种部件最初地由金属或碳制成。
然而，随着复合材料的使用变得越来越普遍，为了减小飞行器的结构的质量，理想的是以低成本并且以允许高生产率的方式利用复合材料生产如上文描述的部件。“复合材料”指的是基于嵌入在用作粘合剂的基质——比如固化的树脂——中的加强纤维的材料。加强纤维可以是金属的或有机性质的。在长形形状的结构部件的特别情况下，比如在上文描述的部件的情况下，优选地使用碳纤维，因为碳纤维具有非常好的机械性能。树脂通常是热固性树脂，例如属于环氧树脂族的热固性树脂。
因此，图3图示了例如源自预浸材料或通过用树脂浸渍得到的复合材料制成的已知类型的加劲件30。这些技术允许产生具有能够沿着部件变化的横截面的部件，如图3a、图3b和图3c所图示的，图3a、图3b和图3c分别示出了在图3的平面A-A、平面B-B和平面C-C上的横截面中的加劲件30。在产生具有恒定的横截面的部件的情况下，这些部件还能够利用拉挤成型来生产。
然而，这些部件的特定区域需要被加强。这些区域一般是涉及将部件固定至飞行器结构的其他元件的区域，比如靠近部件的端部的区域，并且有时是位于这些部件的中间的一个或更多个区域。
出于这个原因，金属加强元件23被附接至这些部件的待被加强的那些区域。这些加强元件23一般通过铆钉连接或螺栓连接而固定到位，从而使得制造这些部件的方法复杂且昂贵。
类似地，图4图示了已知类型的以复合材料制成为单件的结构联杆24。考虑到这种连杆的端部28的通常复杂的形状，这种连杆的制造同样地需要复杂且昂贵的方法。
发明内容
本发明的主要目的是提供针对这些问题的简单经济且有效的解决方案。
为此，本发明提出用于制造用于飞行器结构的由复合材料制成的长形整体形状的部件的方法，所述方法包括以下步骤：
-由包含嵌入至可聚合树脂中的加强纤维的第一复合材料产生拉挤成型的预成形件，使得所获得的预成形件的树脂处于部分聚合的状态；
-利用包含嵌入至可聚合树脂中的加强纤维的第二复合材料产生至少一个加强元件，使得所获得的加强元件的树脂处于部分聚合的状态；随后
-将所述至少一个加强元件应用至预成形件的待被加强的区域；随后
-完成属于由预成形件和所述至少一个加强元件形成的组件的树脂的聚合；以及
-因此，获得用于飞行器结构的由复合材料制成的具有通过所述至少一个加强元件加强的至少一个部分的部件。
因此，本发明提出利用由复合材料制成的预成形件产生结构部件，该预成形件通过拉挤成型生产并且由复合材料制成的加强元件加强，这些加强元件通过共固化连接至预成形件。应理解的是，预成形件的树脂的聚合和所述至少一个加强元件的树脂的聚合是共同完成的。
根据标准术语，术语“预成形件”指示整体上具有明确的形状的结构，尽管该结构的准确形状会随后被潜在的机械加工操作而改变。因此，在所有情况下，预成形件整体上具有在过程结束时所获得的部件的形状。特别地，在使用拉挤成型产生该预成形件的步骤之后，预成形件的整体曲率不会改变。
此外，“使用拉挤成型产生”和“产生拉挤成型的预成形件”指的是预成形件通过将加强纤维拉动通过模具而获得，其中，该模具的横截面或多或少与预成形件的横截面互相补充，除了考虑在使用纤维缠绕技术的情况下这种预成形件的可能的变厚的情况，如将在下文变得更明显的。
因此，总体上，本发明能够获益于拉挤成型技术的简单和低成本，同时由于共固化技术而确保了在加强元件与部件的剩余部分之间的最优质量的结合。此外，这种结合的质量可以使用常规的非损伤性试验装置来检查，尤其是使用超声波类型的非损伤性试验装置。
根据本发明的方法特别地能够独立于部件的剩余部分来加强部件的特定区域。
优选地，部件是机身纵向加劲件或地板横向构件或地板轨道或地板支承支柱或结构联杆。
此外，预成形件有利地具有至少一个端部，该至少一个端部意在用于固定部件并且用于构成待加强的所述区域，其中，所述至少一个加强元件应用至待加强的区域。
此外，该方法优选地包括如下随后的步骤：穿透部件的所述加强部分形成至少一个孔口。
在那种情况下，该方法优选地包括如下随后的步骤：将线缆或管或紧固件穿过孔口。
作为替代方案，孔口可以不使用并且具有减轻部件的质量的唯一功能。
在本发明的第一优选的实施方式中，所述至少一个加强元件具有平面形状并且被应用至预成形件的平面部分。
在本发明的第二优选的实施方式中，预成形件具有封闭的横截面，并且所述至少一个加强元件通过推入配合被应用至预成形件的待加强的区域。
优选地，预成形件具有管状形状，并且所述至少一个加强元件的至少一部分具有能够与预成形件推入配合在一起的管状形状。
优选地，所述至少一个加强元件包括两个管状形状的加强元件，并且所述加强元件分别推入配合至预成形件的两个相反的端部中或推入配合在所述两个相反的端部上，其中，该两个相反的端部优选地形成固定接合面。
优选地，使用拉挤成型产生预成形件包括纤维缠绕的步骤。
总体上，该方法有利地包括如下随后的步骤：对所述部件进行机械加工，特别地在所述至少一个加强元件的区域中进行机械加工。
优选地，在包括完成预成形件和加强元件这两者的组件的聚合的步骤之前，预成形件的聚合度和加强元件的聚合度介于10％与50％之间，优选地介于20％与30％之间。
优选地，所述至少一个加强元件还利用拉挤成型产生。
附图说明
通过阅读以非限制性示例给出的下列描述并且参照附图，将更好地理解本发明并且本发明的另外的细节、优点和特征将变得明显，在附图中：
-图1为已经描述的已知类型的飞行器机身部段的示意性立体图；
-图2为已经描述的已知类型的飞行器中央翼盒的部分立体示意图；
-图3为已经描述的已知类型的飞行器的加劲件的示意性侧视图；
-图3a、图3b和图3c为已经描述的分别在图3的平面A-A、平面B-B和平面CC上的图3的加劲件的横截面中的示意图；
-图4为已经描述的用于已知类型的飞行器的结构联杆的示意性侧视图；
-图5为用于实现根据本发明的第一实施方式的制造用于飞行器结构的由复合材料制成的部件的方法的拉挤成型装置的示意图；
-图6为通过根据本发明的第一实施方式的方法制造的用于飞行器结构的由复合材料制成的部件的部分立体示意图；
-图7为用于实现根据本发明的第二实施方式的制造用于飞行器结构的由复合材料制成的部件的方法的拉挤成型装置的示意图；
-图8a为在实现根据本发明的第二实施方式的方法的过程中通过拉挤成型生产的由复合材料制成的预成形件的示意性侧视图；
-图8b为在图8a的预成形件的图8a的A-A上的轴向截面中的示意图；
-图9a为意在形成加强元件并且在实现根据本发明的第二实施方式的方法的过程中通过拉挤成型产生的由复合材料制成的第二成型件的示意性侧视图；
-图9b为图9a的第二成型件在图9a的B-B上的轴向截面中的示意图；
-图10a为在实现根据本发明的第二实施方式的方法的过程中通过对图9a的第二成型件进行机械加工而获得的加强元件的示意性侧视图；
-图10b为图10a的加强元件在图10a的C-C上的轴向截面中的示意图；
-图11a为由图8a的预成形件和图10a的加强元件形成的组件的示意性侧视图，该图10a的加强元件在实现根据本发明的第二实施方式的方法的过程中被推入配合至图8a的预成形件的一个端部中；
-图11b为图11a中可见的组件的图11a的D-D上的轴向截面中的示意图；
-图12a为在实现根据本发明的第二实施方式的方法的结束时通过对图11a的组件进行机械加工而获得的部件的示意性侧视图；
-图12b为图12a中可见的部件的图12a的E-E上的轴向截面中的示意图；以及
-图13a至图17b为分别与图8a至图12b相似的视图并且图示了实现根据本发明的第二实施方式的方法的替代方法。
贯穿这些附图，相同的附图标记可以指示相同或相似的元件。
具体实施方式
根据本发明的方法意在总体上用于制造用于飞行器结构的由复合材料制成的部件。该方法特别地涉及制造长形整体形状的部件，比如机身纵向加劲件、地板横向构件、地板轨道、地板支承支柱或甚至结构联杆。
图5非常示意性地图示了已知类型的自身允许实现根据本发明的第一实施方式的方法的拉挤成型装置50。
这种装置50包括支承单元52、浸注单元54、固化单元56、牵引单元58以及锯切单元60，该支承单元52用于支承强化纤维比如碳纤维的绷架(reel)。
根据本发明的第一实施方式的方法首先包括使用拉挤成型装置50利用包含嵌入至可聚合树脂——比如热固性环氧树脂类型的树脂——中的加强纤维的第一复合材料制造预成形件，并且使得所获得的预成形件的树脂处于部分聚合的状态。
为此，加强纤维62被逐渐从支承单元52放出以进入浸注单元54，在浸注单元54处，加强纤维62被浸注有可聚合树脂，之后，纤维继续行进通过固化单元56，在固化单元56中，浸注有树脂的纤维通过对预成形件的横截面进行限定的模具而定形状，并且树脂的部分聚合被预形成，优选地使得当纤维离开固化单元56时聚合度介于10％与50％之间，该聚合度优选地介于20％与30％之间。贯穿该过程，通过牵引单元58提供对加强纤维的牵引，这种牵引使得这些纤维被放出。最后，锯切单元60允许当纤维离开固化单元56时被切断成具有期望长度的预成形件64。
因此，所产生的预成形件具有例如C形、I形、L形、Z形或欧米茄形形状的横截面。
在产生如上文说明的预成形件64之前或之后，或在产生预成形件64的同时，该方法包括产生由包含嵌入在可聚合树脂中的加强纤维的第二复合材料制成的一个或更多个加强元件或补片，使得所获得的每个加强元件的树脂同样地处于部分聚合的状态中，优选地同样处于介于10％与50％之间的聚合度，该聚合度还优选地介于20％与30％之间。
在图示的示例中，加强元件由拉挤成型装置50或类似的装置制成，并且第二复合材料与第一复合材料类似，这意味着预成形件64的纤维和树脂与加强元件的纤维和树脂分别具有相同的特性。加强元件例如呈板或盘的形式，如将在下文中变得更明显的。
该方法接下来包括将每个加强元件应用至预成形件64的待加强的区域。
为此，使用对本领域技术人员而言已知的技术例如真空袋或真空囊将大约1巴或更大的压力施加至每个加强元件，从而使加强元件保持在预成形件64上。优选地当预成形件的所有表面与每个加强元件接触时产生真空。因此，能够尽可能地限制分层或产生气孔的风险。此外，优选地通过金属模具提供所形成的部件的最终的几何形状。
因此获得的组件被随后放置在高压锅或烤箱中以便完成形成预成形件64和每个加强元件的材料的树脂的聚合，优选地使得获得树脂的大于或等于95％的聚合度。
作为替代方案，可以通过热形成按压件完成受到压力的树脂的聚合，因此使得能够避免使用真空袋和高压锅。
因此，总体上，预成形件64与每个加强元件之间的结合通过共固化来实现。
图6图示了借助于上述方法所获得的部件的端部。在图示的示例中，部件是具有I形横截面的地板支承支柱70，即，地板支承支柱70包括两个基底部72，所述两个基底部72基本上彼此平行并且通过基本上与基底部72正交的腹板74而彼此连接。
地板支承支柱70的端部包括两个加强元件76和78，所述两个加强元件76和78在腹板74的待加强的两个区域处叠覆在支柱70的腹板74上并且通过共固化结合至腹板74。因此，在该示例中，加强元件和待加强的区域具有平面形状。
作为示例，加强元件76呈矩形板的形式，而加强元件78呈盘的形式并且还与腹板74一起被开孔以形成穿透支柱70的孔口80，从而允许管线、线缆、管道或管的通过，或替代性地用于紧固件(图6中未描绘)的通过，或仅为了减轻支柱70的质量。用于加强孔口80的边缘的加强元件78的质量实际上可能显著地低于腹板74的在形成孔口80时所移除的部分的质量。
可以如图6中所描绘的使用加强元件76以便增大腹板74的需要被加强的区域中的厚度。
作为替代方案，加强元件76可以随后穿透有一个或更多个孔口，例如用于使一个或更多个紧固件(图6中未描绘)穿过。因此，加强元件76使得能够提高腹板74的强度，尤其是在考虑到敲击力的情况下能够提高腹板74的强度。
图7非常示意性地图示了已知类型的本身用于实现根据本发明的第二实施方式的方法的拉挤成型装置90。该拉挤成型装置90整体上与图3的拉挤成型装置50类似，但与拉挤成型装置50的区别至少在于，该拉挤成型装置90还包括纤维缠绕单元92。
在图示的示例中，纤维缠绕单元92定位在预制模具93和浸注单元54之间。
因此，拉挤成型装置90允许使用具有纤维缠绕——通常称为“拉动缠绕”——的拉挤成型技术，在该技术中，支承单元52供给纵向加强纤维62，纵向加强纤维62穿过预制模具93从而允许产生具有封闭的横截面的预成形件，例如圆形横截面，而纤维缠绕单元92允许周向的加强纤维94围绕由纵向纤维62形成的预成形件缠绕，并且因此允许增大预成形件的厚度。
根据本发明的第二实施方式的使用拉挤成型装置90实现的方法在获得管状整体形状的部件方面是特别有利的。
作为示例，图8a至图12b图示了使用该方法产生结构联杆95。
该方法首先包括使用拉挤成型装置90利用包含嵌入至可聚合树脂中的加强纤维的第一复合材料制造预成形件96(图8a和图8b)，并且使得所获得的预成形件的树脂处于部分聚合的状态。
为此，纵向加强纤维62被逐渐从支承单元52放出并且通过穿过预制模具93而形成管状组件，并且周向的加强纤维94被渐进地从纤维缠绕单元92放出并且围绕上文提到的管状组件缠绕，随后，组件进入浸注单元54，在浸注单元54处，加强纤维62和94被浸注有可聚合树脂，之后，浸注有树脂的加强纤维继续行进通过固化单元56，在固化单元56中，模具使得组件定形状并且发生树脂的部分聚合，优选地使得当纤维离开固化单元56时树脂的聚合度介于10％与50％之间，该聚合度优选地介于20％与30％之间。贯穿该过程，通过牵引单元58提供对加强纤维的牵引，这种牵引使得这些纤维被放出。最后，锯切单元60允许当纤维离开固化单元56时被切断成具有期望长度的主成型件96。
因此生产的预成形件96具有管状形状，例如具有圆形的横截面，如图8a和图8b图示的。
在产生如上文说明的预成形件96之前或之后，或在产生预成形件96的同时，该方法包括产生由包含嵌入在可聚合树脂中的加强纤维的第二复合材料制成的一个或更多个加强元件98(图10a和图10b)，使得所获得的每个加强元件的树脂同样地处于部分聚合的状态中，优选地同样处于介于10％与50％之间的聚合度，该聚合度还优选地介于20％与30％之间。
在图示的示例中，加强元件98由通过拉挤成型装置90或类似的装置生产的第二预成形件100(图9a和图9b)制造而成，并且第二复合材料与第一复合材料类似，这意味着预成形件96的纤维和树脂与加强元件98的纤维和树脂分别具有相同的性质。此外，在该示例中，加强元件98的数量为两个并且两个加强元件98彼此类似，在附图中仅描绘了一个加强元件98。
更具体地，意在形成加强元件98的第二预成形件100(图9a和图9b)优选地以与预成形件96相同的方式制造。然而第二预成形件100具有比预成形件96的长度更短的长度并且具有基本上补充预成形件96的内部截面的形状的外部截面，使得能够允许第二预成形件100随后一起推入配合至预成形件96的两个相反的端部102中。
加强元件98的制造随后包括对每个第二预成形件100的内表面进行机械加工使得在该内表面中形成有截头圆锥部104，该截头圆锥部104的横截面随着距离第二预成形件100的一个轴向端部106的变远而变宽(图10b)。因此，图10a和图10b示出了在对相应的第二预成形件100机械加工之后所获得的加强元件98。
该方法接下来包括将每个加强元件98应用至预成形件96的待加强的区域。
更具体地，这种操作在该情况下包括将两个加强元件98推入配合至预成形件96的两个相反的端部102中的相对应的一个端部中，如图11a和图11b所图示的。
可选地，加强元件98可以事先沿其纵向方向切有裂口以便使得加强元件98更易于推入配合至预成形件96中。
接下来，大约1巴或更大的压力径向地朝向外侧被施加至每个加强元件的内部表面，使得能够保持加强元件的表面与预成形件96的表面接触。压力例如通过真空囊或袋被施加。预成形件96优选地以配合的圆筒形的形式被接合，这使得反压力被施加至预成形件96的外部表面。优选地，当预成形件的所有表面与每个加强元件的表面接触时，产生真空。以这种方式，能够尽可能地限制分层或出现气孔的风险。
因此所获得的组件被随后放在高压锅或烤箱中以便完成形成预成形件96和每个加强元件98所使用的材料的树脂的聚合，优选地使得获得树脂的大于或等于95％的聚合度。
作为替代方案，可以通过热形成按压件完成受到压力的树脂的聚合，因此使得能够避免使用真空袋和高压锅。
因此，总体上，预成形件96与每个加强元件98之间的结合通过共固化来实现。
在图示的示例中，每个加强元件98的截头圆锥部104使得能够避免连杆95的内表面中的不连续。
该方法接下来并且可选地包括机械加工步骤。在产生结构联杆95的特定的情况下，机械加工特别地涉及针对部件的端部使得能够形成固定的轭部108。为此，在结构联杆95的相对应的纵向端部上加工出两个纵向狭槽110，并且随后在连杆中穿透有通透的切口，该通透的切口沿着基本上与纵向狭槽110的平面E-E正交的方向穿过由加强元件98强化的端部102。
如图12b所示，加强元件98产生结构联杆95的在其端部102处的内部表面的附加的厚度。
图13a至图17b图示了使用根据上文描述的第二实施方式的方法的替代形式产生结构联杆95a。
在该替代形式中，第二预成形件100a(图14a和图14b)具有基本上补充预成形件96(图13a和图13b)的外部横截面的形状的内部横截面，使得允许预成形件96的两个相反的端部102随后被推入配合至相对应的第二预成形件100a中。
此外，加强元件98a的机械加工在每个第二预成形件100a的外部表面上进行，使得能够在该外部表面中形成截头圆锥部104a，该截头圆锥部104a的横截面远离于第二预成形件100a的轴向端部106a而变宽(图15a和图15b)。
将每个加强元件98a应用至预成形件96的待加强的区域的操作随后包括将两个加强元件98a推入配合在预成形件96的两个相反的端部102的相对应的一个端部上，如图16a和图16b中图示的。可选地，加强元件98a可以沿其纵向方向被事先切有裂口，以便更容易地将加强元件98a推入配合在预成形件96上。
在这种情况下使用的配合形式可以是接合在预成形件96的内侧的心轴。
所获得的部件可以随后被机械加工，例如用于如在上文描述的连杆95的情况下那样产生狭槽110a并且形成轭部108a。
应指出的是，在该示例中，加强元件98a在结构联杆95a的外部表面上产生附加的厚度。
在这种情况下，每个加强元件98a的截头圆锥部104a使得能够避免在连杆95a的外部表面中的不连续。
总体上，因此，根据本发明的方法使得能够以简单且廉价的方式获得长形整体形状的由复合材料制成的部件，其中，该长形整体形状具有相对复杂的形状。
此外，应指出的是，在上文描述的方法中，多轴线织物可以被定位且导引通过拉挤成型装置，使得多轴线织物变得叠覆有加强纤维62。如本领域技术人员已知的，这种织物包括沿着相对于由加强纤维62限定的纵向方向倾斜的一些方向定向的纤维。

Claims (9)

1.一种用于制造用于飞行器结构的由复合材料制成的长形整体形状的部件(70、95、95a)的方法，其特征在于，所述方法包括以下步骤：
-由包含嵌入至可聚合树脂中的加强纤维(62、94)的第一复合材料产生拉挤成型的预成形件(64、96)，使得所获得的所述预成形件的树脂处于部分聚合的状态；
-单独利用包含嵌入至可聚合树脂中的加强纤维(62、94)的第二复合材料产生至少一个加强元件(76、78、98、98a)，使得所获得的所述加强元件的树脂处于部分聚合的状态；随后
-将所述至少一个加强元件应用至所述预成形件(64、96)的待加强的区域(74、102)，其中，在完成聚合之前，在所述预成形件的待加强的区域处对所述至少一个加强元件施加压力以将所述至少一个加强元件保持就位；随后
-完成属于由所述预成形件(64、96)和所述至少一个加强元件(76、78、98、98a)形成的组件的树脂的聚合从而将所述加强元件(76,78,98,98a)直接附接至所述预成形件(64,96)；以及
-因此获得用于飞行器结构的复合材料的部件(70、95、95a)，其中，所述部件(70、95、95a)具有至少一个通过所述至少一个加强元件加强的部分,
其中，所述部件为机身纵向加劲件或地板横向构件或地板轨道或地板支承支柱或结构联杆，
其中，在包括完成所述预成形件和所述加强元件这两者的组件的聚合的步骤之前，所述预成形件的聚合度和所述加强元件的聚合度介于10％与50％之间。
2.根据权利要求1所述的方法，其中，所述预成形件具有至少一个端部，所述至少一个端部用于固定所述部件并且构成待加强的所述区域，其中，所述至少一个加强元件(76、78、98、98a)被应用至待加强的所述区域。
3.根据权利要求1所述的方法，包括以下随后的步骤：穿透所述部件的被加强的所述部分形成至少一个孔口(80)。
4.根据权利要求3所述的方法，包括以下随后的步骤：将线缆或管或紧固件穿过所述孔口(80)。
5.根据权利要求1至4中的任一项所述的方法，其中，所述至少一个加强元件(76、78)具有平面形状并且被应用至所述预成形件(64)的平面部分(74)。
6.根据权利要求1至4中的任一项所述的方法，其中，所述预成形件(96)具有封闭的横截面，并且，所述至少一个加强元件(98、98a)通过推入配合而被应用至所述预成形件(96)的待加强的所述区域(102)。
7.根据权利要求6所述的方法，其中，所述预成形件(96)具有管状形状，并且所述至少一个加强元件(98、98a)的至少一部分具有能够与所述预成形件推入配合在一起的管状形状。
8.根据权利要求7所述的方法，其中，所述至少一个加强元件(98、98a)包括两个管状形状的加强元件，并且，所述加强元件分别推入配合至所述预成形件(96)的两个相反的端部(102)中或推入配合在所述两个相反的端部(102)上，其中，所述两个相反的端部(102)形成固定接合面。
9.根据权利要求1至4中的任一项所述的方法，其中，所述至少一个加强元件(76、78、98、98a)利用拉挤成型产生。
CN201510232363.2A 2014-05-09 2015-05-08 制造用于飞行器结构的由复合材料制成的部件的方法 Active CN105082575B (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1454182A FR3020780B1 (fr) 2014-05-09 2014-05-09 Procede de fabrication d'une piece en materiau composite pour structure d'aeronef par pultrusion et cocuisson
FR1454182 2014-05-09

Publications (2)

Publication Number Publication Date
CN105082575A CN105082575A (zh) 2015-11-25
CN105082575B true CN105082575B (zh) 2020-07-31

Family

ID=50976963

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201510232363.2A Active CN105082575B (zh) 2014-05-09 2015-05-08 制造用于飞行器结构的由复合材料制成的部件的方法

Country Status (4)

Country Link
US (1) US9796142B2 (zh)
JP (1) JP6680465B2 (zh)
CN (1) CN105082575B (zh)
FR (1) FR3020780B1 (zh)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP6667391B2 (ja) * 2016-07-06 2020-03-18 三菱重工業株式会社 複合材、引抜成形装置及び引抜成形方法
DE102016219303A1 (de) * 2016-10-05 2018-04-05 Zf Friedrichshafen Ag Fahrwerksbauteil in Faserkunststoffverbund-Monobauweise mit duroplastischem Matrixwerkstoff und Verfahren zu dessen Herstellung
JP6906794B2 (ja) * 2017-12-26 2021-07-21 日本総合リサイクル株式会社 解体作業車
JP7149151B2 (ja) 2018-10-03 2022-10-06 川崎重工業株式会社 複合材料製航空機用部品およびその製造方法
JP7199940B2 (ja) 2018-12-03 2023-01-06 川崎重工業株式会社 複合材料製航空機用部品およびその製造方法
EP3972749A4 (en) * 2019-06-20 2024-01-17 Galactic Co., LLC DRAW EXTRUSION OF PROFILES WITH NON-UNIFORM CROSS SECTIONS
IT201900015509A1 (it) * 2019-09-03 2021-03-03 Leonardo Spa Dispositivo di stampaggio a compressione di parti in materiale composito a partire da lastre in composito a matrice termoplastica

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101189118A (zh) * 2005-06-07 2008-05-28 空中客车德国有限公司 制造用于形成航空器用部件的增强壳体的方法以及用于航空器用部件的壳体
US20130112309A1 (en) * 2011-11-03 2013-05-09 The Boeing Company Tubular Composite Strut Having Internal Stiffening and Method for Making the Same

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3979709A (en) * 1975-05-22 1976-09-07 The Chase-Shawmut Company Electric fuse having a multiply casing of a synthetic - resin glass-cloth laminate
JPS6021853B2 (ja) * 1981-08-03 1985-05-29 日東電工株式会社 連続成形方法
JPS61195825A (ja) * 1985-02-27 1986-08-30 Central Glass Co Ltd Ｆｒｐ成形用素材およびこれを用いるｆｒｐ曲げ成形法
US5609806A (en) * 1994-06-28 1997-03-11 Reichhold Chemicals, Inc. Method of making prepreg
JP4316059B2 (ja) * 1999-08-06 2009-08-19 富士重工業株式会社 複合材翼の製造方法
JP4318381B2 (ja) * 2000-04-27 2009-08-19 本田技研工業株式会社 繊維強化複合材からなる胴体構造体の製造方法、及びそれにより製造される胴体構造体
JP4425424B2 (ja) * 2000-05-01 2010-03-03 本田技研工業株式会社 繊維強化複合材からなるジョグル付き半硬化物品の製造方法、及びそれを用いた予備成形構造体の製造方法
EP1621323A1 (en) * 2004-07-27 2006-02-01 Hexcel Composites GmbH Continuous pultrusion process for producing high performance structural profiles
DE102007015909A1 (de) * 2007-04-02 2008-10-09 Mt Aerospace Ag Verfahren zur Herstellung faserverstärkter Hohlkörper
US8114329B2 (en) * 2008-03-03 2012-02-14 Abe Karem Wing and blade structure using pultruded composites
US8883908B2 (en) * 2009-06-02 2014-11-11 Johns Manville Methods for making reinforced thermoplastic composites using reactive fibers and/or reactive flakes
EP2266788A1 (fr) * 2009-06-26 2010-12-29 Bd Invent S.A. Procédé de fabrication de bielles composites et bielles obtenues selon le procédé
MX2012011052A (es) * 2010-03-25 2013-02-26 Epsilon Composite Procedimiento para la realizacion en continuo de una pieza de union de material compuesto.
FR2981653B1 (fr) * 2011-10-25 2014-08-22 Arkema France Materiau composite thermoplastique renforce de fibres synthetiques et procede de fabrication
FR2984794A1 (fr) * 2011-12-22 2013-06-28 Epsilon Composite Piece en materiau composite a protection integree contre un impact mecanique
FR2984796A1 (fr) * 2011-12-22 2013-06-28 Epsilon Composite Procede de pultrusion ameliore par vibrations et dispositif de mise en oeuvre

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN101189118A (zh) * 2005-06-07 2008-05-28 空中客车德国有限公司 制造用于形成航空器用部件的增强壳体的方法以及用于航空器用部件的壳体
US20130112309A1 (en) * 2011-11-03 2013-05-09 The Boeing Company Tubular Composite Strut Having Internal Stiffening and Method for Making the Same

Also Published As

Publication number Publication date
CN105082575A (zh) 2015-11-25
JP6680465B2 (ja) 2020-04-15
JP2015214151A (ja) 2015-12-03
US9796142B2 (en) 2017-10-24
FR3020780A1 (fr) 2015-11-13
FR3020780B1 (fr) 2017-01-13
US20150321429A1 (en) 2015-11-12

Similar Documents

Publication Publication Date Title
CN105082575B (zh) 制造用于飞行器结构的由复合材料制成的部件的方法
KR101786342B1 (ko) 멀티박스 날개 보 및 표면
CN103370185B (zh) 包括带有平滑尾段的集成加筋件的复合材料结构及其制造方法
EP2301840B1 (en) Integrated aircraft structure in composite material
JP5801885B2 (ja) 一体型補剛材を有する複合構造物およびその作製方法
US9359060B2 (en) Laminated composite radius filler with geometric shaped filler element and method of forming the same
EP2203288B1 (en) A method of manufacturing a curved structural element made of composite material and having a complex, open cross-section
US20100038030A1 (en) Advanced composite aerostructure article having a braided co-cured fly away hollow mandrel and method for fabrication
JP2010524718A (ja) 連続したプロファイルを作製するための引抜き成形法
EP3483057B1 (en) Reinforcing arrangement for an opening in an aircraft structure
US10549490B2 (en) Method for manufacturing a stiffened panel made from composite material
EP2774854A1 (en) An improved monolithic fan cowl of an aircraft engine and a manufacturing method thereof
EP2746038B1 (en) Method for the production of a structural component, structural component, shell, and aircraft or spacecraft
US9358733B2 (en) Method and a device for the manufacture of a fibre composite component, and a fibre composite component
US11267584B2 (en) Method for manufacturing a rear section of an aircraft and aircraft rear section
US20210155336A1 (en) Bulb stiffener with sinusoidal web

Legal Events

Date Code Title Description
C06 Publication
PB01 Publication
SE01 Entry into force of request for substantive examination
SE01 Entry into force of request for substantive examination
GR01 Patent grant
GR01 Patent grant