IT202000028046A1 - Metodo e dispositivo per la fabbricazione di un elemento strutturale in materiale composito con profilo a z - Google Patents

Metodo e dispositivo per la fabbricazione di un elemento strutturale in materiale composito con profilo a z

Info

Publication number
IT202000028046A1
IT202000028046A1 IT102020000028046A IT202000028046A IT202000028046A1 IT 202000028046 A1 IT202000028046 A1 IT 202000028046A1 IT 102020000028046 A IT102020000028046 A IT 102020000028046A IT 202000028046 A IT202000028046 A IT 202000028046A IT 202000028046 A1 IT202000028046 A1 IT 202000028046A1
Authority
IT
Italy
Prior art keywords
final
configuration
structural element
composite material
final configuration
Prior art date
Application number
IT102020000028046A
Other languages
English (en)
Inventor
Nicola Gallo
Stefano Giuseppe Corvaglia
Nicola Miani
Luca Monopoli
Antonio Ruberto
Marco Barile
Original Assignee
Leonardo Spa
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 Leonardo Spa filed Critical Leonardo Spa
Priority to IT102020000028046A priority Critical patent/IT202000028046A1/it
Priority to AU2021381060A priority patent/AU2021381060A1/en
Priority to EP21830762.7A priority patent/EP4247626A1/en
Priority to CN202180078849.9A priority patent/CN116867640A/zh
Priority to KR1020237021340A priority patent/KR20230123973A/ko
Priority to PCT/IB2021/060870 priority patent/WO2022107109A1/en
Priority to US18/037,469 priority patent/US20240076060A1/en
Priority to CA3199110A priority patent/CA3199110A1/en
Priority to JP2023530899A priority patent/JP2023551212A/ja
Publication of IT202000028046A1 publication Critical patent/IT202000028046A1/it

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
    • B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
    • 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
    • B29C53/00—Shaping by bending, folding, twisting, straightening or flattening; Apparatus therefor
    • B29C53/02—Bending or folding
    • B29C53/04—Bending or folding of plates or 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
    • B29C70/40—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
    • 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
    • B29C70/461—Rigid movable compressing mould parts acting independently from opening or closing action of the main mould
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • B29C70/541—Positioning reinforcements in a mould, e.g. using clamping means for the reinforcement
    • 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
    • B29C70/544—Details of vacuum bags, e.g. materials or shape
    • 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
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/064—Stringers; Longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • 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
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0072—Fuselage structures substantially made from particular materials from composite materials
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Manufacturing & Machinery (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Robotics (AREA)
  • Transportation (AREA)
  • Moulding By Coating Moulds (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Laminated Bodies (AREA)

Description

DESCRIZIONE
del brevetto per invenzione industriale dal titolo:
METODO E DISPOSITIVO PER LA FABBRICAZIONE DI UN ELEMENTO STRUTTURALE IN MATERIALE COMPOSITO CON PROFILO A Z
La presente invenzione ? altres? relativa ad un dispositivo per la fabbricazione di un elemento strutturale in materiale composito estendentesi lungo una direzione longitudinale rettilinea o curvilinea e avente una sezione trasversale rispetto alla direzione longitudinale conformata a Z, in particolare un elemento strutturale in materiale composito utilizzato in campo aeronautico e facente parte della struttura di un velivolo, ad esempio una trave, un corrente, un composito determinano problemi di accoppiamento galvanico con annessi rischi di corrosione del metallo e necessit di aumentare i livelli di ispezione. Ci comporta un aumento dei costi totali per i produttori di tali componenti e, dunque, per le compagnie aeree.
Nasce dunque l esigenza di realizzare tali elementi strutturali anch essi in materiale composito.
L utilizzo del materiale composito permette di solitamente con l ausilio del vuoto: in tal modo, gli strati vengono compattati e si imprime all elemento strutturale la forma desiderata (ad esempio un profilo a T, a Z, a C, ad omega, eccetera).
L assieme cos formato viene successivamente sottoposto ad un processo di cura su di uno stampo di cura mediante applicazione di pressione e temperatura l ausilio manuale di alcun operatore.
OGGETTO E RIASSUNTO DELL INVENZIONE
Scopo della presente invenzione ? quello di fornire un metodo per la fabbricazione di un elemento strutturale in materiale composito estendentesi lun trasversale a Z di tipo noto.
Secondo l invenzione, questo scopo viene raggiunto da un dispositivo per la fabbricazione di un elemento strutturale in materiale composito con sezione trasversale a Z come rivendicato nella rivendicazione 8.
forma di realizzazione della presente invenzione e durante tre successive condizioni operative;
- le figure 5a-5c illustrano schematicamente, in vista parzialmente sezionata e con parti rimosse per profilo a Z ed ? un elemento multistrato utilizzato in campo aeronautico e facente parte della struttura di un velivolo (non illustrato), ad esempio una trave, un corrente, un longherone o simili della fusoliera di un aeromobile, cui al presente descrizione far riferimento senza per questo perdere in generalit .
In una forma di realizzazione non illustrata, l elemento strutturale 2 potrebbe estendersi lungo una ortogonalmente da porzioni di estremit opposte dell anima 2a in rispettive direzioni opposte tra loro.
La direzione longitudinale D presenta un raggio di curvatura R non nullo.
In una forma di realizzazione non illustrata, le ali 2b, 2c potrebbero estendersi dall anima 2a ad un determinato angolo finale diverso da 90 , ad esempio, ma non esclusivamente, 30 , 45 , 60 , 80 , 85 , ecc.
definito da un materiale composito includente fibre disperse in una matrice polimerica termoindurente.
La figura 2 illustra l elemento strutturale 2 in una sua configurazione finale ed ottenuto mediante il dispositivo 1.
Il dispositivo 1 comprende uno stampo di formatura che porta una porzione sagomata 4.
Con riferimento alle figure 1, 3 e 4a-4c, l elemento strutturale 2 viene ottenuto disponendo, preferibilmente per mezzo di una movimentazione - una seconda ala 2c sia disposta in una propria da una superficie esterna di formatura della porzione fissa 5 e in parte da una superficie esterna di formatura della porzione mobile 6.
Come visibile nelle
particolare per piegare, la seconda ala 2c dalla configurazione iniziale alla configurazione finale, ovvero alla configurazione in cui essa definisce il suddetto angolo finale, preferibilmente un angolo retto guidare la porzione mobile 6 per definire la traslazione lineare della stessa.
Alternativamente, i mezzi attuatori 7 potrebbero comprendere un attuatore elettrodinamico, ad esempi durante la piegatura della seconda ala 2c.
In una forma di realizzazione, i mezzi ad infrarossi sono portati dal robot 20.
Convenientemente, il dispositivo 1 comprende laminazione e la formatura dell elemento strutturale 2 secondo la modalit? sopra descritta, l elemento strutturale 2 ? disposto, in uso e secondo una modalit nota e non descritta in dettaglio, in un dispositiv Dal momento che il dispositivo 1 ? simile, strutturalmente e funzionalmente, al dispositivo 1, esso verr descritto nel seguito unicamente negli aspetti in modo automatizzato, tra la posizione di riposo e la posizione di piegatura mediante il pistone 8 , compiendo una rotazione imperniata attorno alla cerniera 12.
porzione mobile 6 e configurati per essere rilasciati, preferibilmente in modo automatizzato, da una posizione azionato manualmente da un operatore.
Tale configurazione permette di ottenere un sistema di comando per il movimento della porzione mobile 6 automatizzato, ad esempio mediante il suddetto robot, Senza l inserto 13 risulterebbe infatti complicato e al metodo qui descritti ed illustrati possono essere

Claims (1)

  1. RIVENDICAZIONI
    1.- Metodo per la fabbricazione di un elemento strutturale (2) in materiale composito estendentesi lungo una direzione longitudinale (D) rettilinea o curvilinea, avente una sezione trasversale rispetto alla direzione longitudinale (D) conformata a Z e comprendente, in configurazione finale, un?anima (2a) centrale e due ali (2b, 2c) estendentisi ad un determinato angolo finale da porzioni di estremit? configurazione finale;
    c) movimentare una porzione mobile (6) di detto stampo di formatura, la quale ? mobile rispetto ad una porzione fissa (5) di detto stampo di formatura, da una posizione di riposo ad una posizione di piegatura;
    d) spostare detta seconda ala (2c) dalla configurazione iniziale in una configurazione finale in cui essa ? a detto angolo finale rispetto alla porzione di anima (2a) disposta nella propria configurazione finale;
    la fase d) di spostare essendo effettuata mediante 6.- Metodo come rivendicato nella rivendicazione 1 o 2, in cui la fase a) di disporre ? effettuata una camera a vuoto (14) delimitata tra un sacco a vuoto (15) e detta porzione sagomata (4); e
    - applicare vuoto all?interno di detta camera a vuoto (14).
    8.- Dispositivo (1, 1?, 1??, 1???) per la alla porzione di anima (2a) disposta nella propria configurazione finale, e che una seconda ala (2c) sia disposta in una propria configurazione iniziale ad un porzione mobile (6) e configurati per essere rilasciati da una posizione deformata ad una posizione indeformata per comandare il movimento della porzione mobile (6) dalla posizione di riposo alla posizione di piegatura.
    11.- Dispositivo (1???) come rivendicato nella composito ? definito da un materiale non curato o precurato includente fibre disperse in una matrice polimerica termoindurente o termoplastica.
IT102020000028046A 2020-11-23 2020-11-23 Metodo e dispositivo per la fabbricazione di un elemento strutturale in materiale composito con profilo a z IT202000028046A1 (it)

Priority Applications (9)

Application Number Priority Date Filing Date Title
IT102020000028046A IT202000028046A1 (it) 2020-11-23 2020-11-23 Metodo e dispositivo per la fabbricazione di un elemento strutturale in materiale composito con profilo a z
AU2021381060A AU2021381060A1 (en) 2020-11-23 2021-11-23 Method and device for manufacturing a structural element in composite material with a z-shaped profile
EP21830762.7A EP4247626A1 (en) 2020-11-23 2021-11-23 Method and device for manufacturing a structural element in composite material with a z-shaped profile
CN202180078849.9A CN116867640A (zh) 2020-11-23 2021-11-23 用于制造具有z形轮廓的复合材料的结构元件的方法和设备
KR1020237021340A KR20230123973A (ko) 2020-11-23 2021-11-23 Z-형 프로파일을 갖는 복합 재료 구조 요소를 제조하기 위한 방법 및 장치
PCT/IB2021/060870 WO2022107109A1 (en) 2020-11-23 2021-11-23 Method and device for manufacturing a structural element in composite material with a z-shaped profile
US18/037,469 US20240076060A1 (en) 2020-11-23 2021-11-23 Method and device for manufacturing a structural element in composite material with a z-shaped profile
CA3199110A CA3199110A1 (en) 2020-11-23 2021-11-23 Method and device for manufacturing a structural element in composite material with a z-shaped profile
JP2023530899A JP2023551212A (ja) 2020-11-23 2021-11-23 Ｚ字形輪郭を伴う複合材料の構造要素を製造するための方法およびデバイス

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IT102020000028046A IT202000028046A1 (it) 2020-11-23 2020-11-23 Metodo e dispositivo per la fabbricazione di un elemento strutturale in materiale composito con profilo a z

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IT202000028046A1 true IT202000028046A1 (it) 2022-05-23

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EP (1) EP4247626A1 (it)
JP (1) JP2023551212A (it)
KR (1) KR20230123973A (it)
CN (1) CN116867640A (it)
AU (1) AU2021381060A1 (it)
CA (1) CA3199110A1 (it)
IT (1) IT202000028046A1 (it)
WO (1) WO2022107109A1 (it)

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CN115107299B (zh) * 2022-07-05 2024-02-09 江西昌兴航空装备股份有限公司 一种垂尾整体梁铺贴方法

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EP2308670A1 (en) * 2009-10-12 2011-04-13 Vestas Wind Systems A/S Fixing device
US20140072775A1 (en) * 2012-09-07 2014-03-13 Airbus Operations Sas Method for producing a profile that has a re-entrant angle in a composite material from a stack of layers of fibres
EP3196006A1 (en) * 2016-01-22 2017-07-26 The Boeing Company Apparatus and method of forming a composite structure
WO2020121648A1 (ja) * 2018-12-10 2020-06-18 三菱重工業株式会社 積層体の成形方法及び成形治具

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GB2486231B (en) * 2010-12-07 2013-04-03 Gkn Aerospace Services Ltd Composite structure

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Publication number Priority date Publication date Assignee Title
DE102008057783B3 (de) * 2008-11-17 2010-02-04 Eads Deutschland Gmbh Vorrichtung und Verfahren zum Umfalten eines zur Herstellung eines Faserverbundbauteils vorgesehenen textilen Halbzeugprofils
EP2308670A1 (en) * 2009-10-12 2011-04-13 Vestas Wind Systems A/S Fixing device
US20140072775A1 (en) * 2012-09-07 2014-03-13 Airbus Operations Sas Method for producing a profile that has a re-entrant angle in a composite material from a stack of layers of fibres
EP3196006A1 (en) * 2016-01-22 2017-07-26 The Boeing Company Apparatus and method of forming a composite structure
WO2020121648A1 (ja) * 2018-12-10 2020-06-18 三菱重工業株式会社 積層体の成形方法及び成形治具

Also Published As

Publication number Publication date
KR20230123973A (ko) 2023-08-24
WO2022107109A1 (en) 2022-05-27
US20240076060A1 (en) 2024-03-07
AU2021381060A1 (en) 2023-06-29
JP2023551212A (ja) 2023-12-07
CA3199110A1 (en) 2022-05-27
EP4247626A1 (en) 2023-09-27
CN116867640A (zh) 2023-10-10

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