US20080203601A1 - Jig and method of manufacturing aircraft frames in a composite material - Google Patents

Jig and method of manufacturing aircraft frames in a composite material Download PDF

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Publication number
US20080203601A1
US20080203601A1 US11/799,324 US79932407A US2008203601A1 US 20080203601 A1 US20080203601 A1 US 20080203601A1 US 79932407 A US79932407 A US 79932407A US 2008203601 A1 US2008203601 A1 US 2008203601A1
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US
United States
Prior art keywords
jig
preforms
curing
injecting
frame
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.)
Abandoned
Application number
US11/799,324
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English (en)
Inventor
Jesus Manuel Martin Martin
Ignacio Jose Marquez Lopez
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 SL
Original Assignee
Airbus Espana SL
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 Espana SL filed Critical Airbus Espana SL
Assigned to AIRBUS ESPANA, S.L. reassignment AIRBUS ESPANA, S.L. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: LOPEZ, IGNACIO JOSE MARQUEZ, MARTIN, JESUS MANUEL MARTIN
Publication of US20080203601A1 publication Critical patent/US20080203601A1/en
Priority to US12/941,774 priority Critical patent/US8329077B2/en
Assigned to AIRBUS OPERATIONS S.L. reassignment AIRBUS OPERATIONS S.L. CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: AIRBUS ESPANA, S.L.
Abandoned legal-status Critical Current

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/28—Shaping operations therefor
    • B29C70/40—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
    • B29C70/48—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 and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
    • B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
    • B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
    • B29C70/06—Fibrous reinforcements only
    • B29C70/08—Fibrous reinforcements only comprising combinations of different forms of fibrous reinforcements incorporated in matrix material, forming one or more layers, and with or without non-reinforced layers
    • B29C70/083—Combinations of continuous fibres or fibrous profiled structures oriented in one direction and reinforcements forming a two dimensional structure, e.g. mats
    • B29C70/085—Combinations of continuous fibres or fibrous profiled structures oriented in one direction and reinforcements forming a two dimensional structure, e.g. mats the structure being deformed in a three dimensional configuration
    • 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
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/001—Profiled members, e.g. beams, sections
    • B29L2031/008—Profiled members, e.g. beams, sections having a longitudinal cross-section
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • B29L2031/3082—Fuselages
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the present invention relates to a jig for the manufacture of composite material frames for aircraft, as well as to a method of manufacturing said frames in a composite material.
  • load frames are structural elements in charge of withstanding and transferring the loads from other structural elements of the aircraft, such as the wings or stabilizers.
  • the manufacture of the frames is carried out by using machined metal structures or shaped sheet metal structures having in which the part that withstands most of the load is reinforced with machined parts.
  • the section that is normally used is obtained in two pieces: on one hand the Z is manufactured, and on the other hand, the brackets which are riveted to the former section are manufactured.
  • This process has the drawback that long assembly times are necessary and that the final weight is much greater than what would be desired.
  • the present invention relates to a jig for the manufacture of aircraft load frames such that the section of the structure of the obtained frames is done in an integrated manner such that the resulting weight is optimized.
  • the manufacturing method proposed by the present invention is carried out by means of a repetitive process with a short times in curing cycles, such that the necessary assembly times are decreased.
  • the present invention develops a jig for the manufacture, by means of injection and curing processes, of composite material frame preforms for aircraft fuselages by using RTM (resin transfer molding) technology. Therefore, two preforms are manufactured, one with a C-shaped section and another one with an L-shaped section, together with the preforms of the stabilization ribs of the web of the frames and the preform of the roving or staple fiber to cover the gap between the C shaped preform and the L shaped preform. These preforms are previously manufactured by any known preform manufacturing process.
  • the present invention develops a method of manufacturing an aircraft load frame in a composite material.
  • aircraft load frames made of a composite material are obtained by means of the jig and the method of manufacture of the present invention with the following advantages:
  • FIG. 1 shows the section of a known metallic aircraft load frame.
  • FIG. 2 shows the section of an aircraft load frame made of a composite material according to the present invention.
  • FIGS. 3 a and 3 b show perspective views of the aircraft load frame made of a composite material that is finished, impregnated and cured with the jig and the method of the present invention.
  • FIG. 4 shows a C-shaped preform of the aircraft load frame made of a composite material according to the invention.
  • FIG. 5 shows an L-shaped preform of the aircraft load frame made of a composite material according to the invention.
  • FIG. 6 shows one preform of the stabilization rib of the web of the aircraft load frame made of a composite material according to the invention.
  • FIG. 7 shows a preform of the roving or staple fiber of the aircraft load frame made of a composite material according to the invention.
  • FIG. 8 shows the integration of the preforms shaping the aircraft load frame made of a composite material according to the invention.
  • FIG. 9 shows a sectional view of the jig for the manufacture of composite material frames for aircraft according to the invention.
  • FIG. 10 shows a perspective view of the jig for the manufacture of composite material frames for aircraft according to the invention.
  • FIG. 11 shows a detail of the stabilization ribs of the web of the composite material frames for aircraft according to the invention.
  • FIG. 12 shows a general view of the vacuum system of the jig for the manufacture of composite material frames for aircraft according to the invention.
  • the present invention relates to a jig for injecting and curing the preforms of an aeronautic fuselage frame 2 made of a composite material.
  • the section to be manufactured is formed by a C-shaped preform ( FIG. 4 ) and by an L-shaped angular preform 4 ( FIG. 5 ), in addition to different stabilization ribs 5 of the web ( FIG. 6 ) and a preform 6 of the roving or staple fiber ( FIG. 7 ).
  • This arrangement of preforms allows the manufacture of aircraft load frames 2 with the parts for joining them to the following frame integrated therewith, as can be seen in FIG. 8 .
  • the preforms are made of fabric and reinforcements with unidirectional tape in the inner flanges to increase their moment of inertia and, consequently, their rigidity.
  • the jig object of the invention comprises the following elements: an injection and curing jig 7 , a vacuum system 8 and a closing and heating system.
  • the injection and curing jig comprises different members:
  • the vacuum system 8 comprises the following elements:
  • the present invention develops a method of manufacturing composite material load frames for aircraft comprising the following steps:

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Composite Materials (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)
  • Moulding By Coating Moulds (AREA)
US11/799,324 2007-02-28 2007-05-01 Jig and method of manufacturing aircraft frames in a composite material Abandoned US20080203601A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US12/941,774 US8329077B2 (en) 2007-02-28 2010-11-08 Method of manufacturing aircraft frames in a composite material

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
ESPCT/ES07/70042 2007-02-28
PCT/ES2007/070042 WO2008104614A1 (es) 2007-02-28 2007-02-28 Utillaje y método de fabricación de cuadernas de aeronave en material compuesto

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US12/941,774 Division US8329077B2 (en) 2007-02-28 2010-11-08 Method of manufacturing aircraft frames in a composite material

Publications (1)

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US20080203601A1 true US20080203601A1 (en) 2008-08-28

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US11/799,324 Abandoned US20080203601A1 (en) 2007-02-28 2007-05-01 Jig and method of manufacturing aircraft frames in a composite material
US12/941,774 Active 2027-05-25 US8329077B2 (en) 2007-02-28 2010-11-08 Method of manufacturing aircraft frames in a composite material

Family Applications After (1)

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US12/941,774 Active 2027-05-25 US8329077B2 (en) 2007-02-28 2010-11-08 Method of manufacturing aircraft frames in a composite material

Country Status (4)

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US (2) US20080203601A1 (es)
EP (1) EP2127855A4 (es)
CN (1) CN101743117B (es)
WO (1) WO2008104614A1 (es)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
ITMI20101072A1 (it) * 2010-06-14 2011-12-15 Automobili Lamborghini Spa Processo e dispositivi per fabbricare prodotti in materiali compositi
CN103455666A (zh) * 2013-08-12 2013-12-18 燕山大学 一种板框式液压机机架预紧梁与c形板接触面结构
EP2321117B2 (de) † 2008-09-12 2017-01-18 MT Aerospace AG Lasttragendes faserverbundstrukturbauteil und verfahren zu dessen herstellung
CN108052974A (zh) * 2017-12-12 2018-05-18 苏州大学 一种故障诊断方法、系统、设备及存储介质
DE102016124966A1 (de) * 2016-12-20 2018-06-21 Deutsches Zentrum für Luft- und Raumfahrt e.V. Bauteilstruktur und Verfahren zur Herstellung derselben

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Publication number Priority date Publication date Assignee Title
DE102010018932B4 (de) * 2010-04-30 2013-06-13 Airbus Operations Gmbh Umfangsversteifung für einen Luftfahrzeugrumpf
FR2975035B1 (fr) * 2011-05-10 2013-06-14 Snecma Moule de compactage et d'injection pour preforme fibreuse destinee a la fabrication d'une aube de redresseur de turbomachine en materiau composite
ES2401517B1 (es) * 2011-05-31 2014-06-18 Airbus Operations S.L. Cuaderna de aeronave en material compuesto.
EP2883688B1 (fr) * 2013-12-13 2021-09-22 Safran Aero Boosters SA Carter annulaire composite de compresseur de turbomachine et procédé d'obtention de celui-ci
ES2681598T3 (es) * 2014-04-30 2018-09-14 Airbus Operations S.L. Método y dispositivo para la fabricación de una pieza de una aeronave en material compuesto
EP3204206B1 (de) * 2014-10-07 2020-12-09 Basf Se Verfahren und vorrichtung zur herstellung von verstärkten kunststoff-bauteilen
CN105643958A (zh) * 2014-11-14 2016-06-08 江西昌河航空工业有限公司 一种复合材料的成形工装及成形方法
JP7172887B2 (ja) * 2019-07-02 2022-11-16 トヨタ自動車株式会社 車体下部構造

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Cited By (8)

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Publication number Priority date Publication date Assignee Title
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ITMI20101072A1 (it) * 2010-06-14 2011-12-15 Automobili Lamborghini Spa Processo e dispositivi per fabbricare prodotti in materiali compositi
CN103455666A (zh) * 2013-08-12 2013-12-18 燕山大学 一种板框式液压机机架预紧梁与c形板接触面结构
DE102016124966A1 (de) * 2016-12-20 2018-06-21 Deutsches Zentrum für Luft- und Raumfahrt e.V. Bauteilstruktur und Verfahren zur Herstellung derselben
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DE102016124966B4 (de) * 2016-12-20 2020-09-24 Deutsches Zentrum für Luft- und Raumfahrt e.V. Bauteilstruktur und Verfahren zur Herstellung derselben
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CN108052974B (zh) * 2017-12-12 2022-05-17 苏州大学 一种故障诊断方法、系统、设备及存储介质

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US8329077B2 (en) 2012-12-11
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EP2127855A4 (en) 2015-07-08
US20110049744A1 (en) 2011-03-03
EP2127855A1 (en) 2009-12-02

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