WO2008121005A1 - Fabrication et assemblage de composant d'aéronef - Google Patents

Fabrication et assemblage de composant d'aéronef Download PDF

Info

Publication number
WO2008121005A1
WO2008121005A1 PCT/NZ2008/000065 NZ2008000065W WO2008121005A1 WO 2008121005 A1 WO2008121005 A1 WO 2008121005A1 NZ 2008000065 W NZ2008000065 W NZ 2008000065W WO 2008121005 A1 WO2008121005 A1 WO 2008121005A1
Authority
WO
WIPO (PCT)
Prior art keywords
moulding
wing
assembly
fuselage
spar
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.)
Ceased
Application number
PCT/NZ2008/000065
Other languages
English (en)
Inventor
Lapo Ancillotti
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.)
FALCOMPOSITE Ltd
Original Assignee
FALCOMPOSITE Ltd
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 FALCOMPOSITE Ltd filed Critical FALCOMPOSITE Ltd
Publication of WO2008121005A1 publication Critical patent/WO2008121005A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

Links

Classifications

    • 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
    • B64C1/26—Attaching the wing or tail units or stabilising surfaces
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/185—Spars
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/24—Moulded or cast structures
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/28—Leading or trailing edges attached to primary structures, e.g. forming fixed slots
    • 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

Definitions

  • the present invention relates to aircraft component manufacture and assembly. More particularly and without wishing to be restrictive the present invention relates to aircraft assemblies or subassemblies, or components for such assemblies or sub assemblies, (formed from composite materials).
  • composite materials refers to a matrix or binder that binds together a reinforcement material or materials.
  • Reinforcement materials include fibres of for example glass, a polymeric material such as KEVLARTM and carbon.
  • Suitable matrix materials include thermosetting plastics (but can be thermosoftening plastics in some instances). Ceramics, carbon and metals have also been used in special applications as a matrix material.
  • US 5476704 discloses a plastics composite profile which permits wing spars with a tapering cross section and constructional height.
  • Kohler discloses a requirement for at least two pre- manufactured flanges and at least one pre-manufactured web interconnecting the flanges, the flanges being manufactured by pultrusion of thermo plastic resin impregnated rovings and having adhesive bonded flanges protruding from the surface of the flanges over part of the height of the web and defining a hollow gap there between.
  • PCT/US2004/011516 (published as WO2005/002961) of Adam Aircraft Industries, Inc refers to the manufacture of composite material aircraft and the requirement for a great number of moulds. They disclose the composite parts generally are manufactured by laying up uncured composite material in a mould or tool, drawing a vacuum on the uncured material, curing the material in die mould at controlled conditions of temperature and humidity, and then removing the part from the mould. They refer to the challenge faced by the composite aircraft designer to reduce the parts to reduce manufacturing and assembly costs and the need for flexibility to change features of parts whilst avoiding large retooling costs.
  • the present invention also relates to a desire to provide alternative assemblies and subassemblies (preferably using one shot) moulded components of a composite material to provide shape and/or structural strength.
  • a composite material to provide shape and/or structural strength.
  • such components are to provide the structure of the resulting assembly ie, both required shape and require structural strength.
  • the present inventions has as a further or alternative object the provision of wing components able to be manufactured and to be assembled with savings in labour.
  • one-shot (eg resin infusion) moulding techniques are to provide readily assemble wing structures.
  • the present invention also is directed to novel wing assemblies, combinations of components for wing assemblies, wing skin mouldings and related aircraft and/ or their compatible fuselages. Preferably at least most are to be of, or primarily of, one-shot (preferably resin infusion) moulded components but optionally with optional localised reinforcement and/or modification post mould and/or during assembly.
  • one-shot preferably resin infusion
  • the invention is a wing assembly, the assembly comprising or including: a first moulding or composite material form (“moulding”) that provides an elongate spar of the wing assembly, a second moulding or composite material form (“moulding”) which provides at least in part a front, top and bottom of the wing assembly thereby to define respectively, at least in part the leading edge, at least in part the fore and rear regions of the upper surface and at least in part the fore region of the under surface, and a third moulding or composite form (“moulding”) defining at least most of the rear under surface.
  • a first moulding or composite material form (“moulding") that provides an elongate spar of the wing assembly
  • a second moulding or composite material form which provides at least in part a front, top and bottom of the wing assembly thereby to define respectively, at least in part the leading edge, at least in part the fore and rear regions of the upper surface and at least in part the fore region of the under surface
  • said third moulding provides a web bounded proximately, distally and rearwardly by upstands from the web, the underside of the web defining at least most of said rear under surface, and the upstands defining a proximate bulkhead, a distal bulkhead and the rear edge.
  • the rear edge upstands from the web of said third moulding and extends between the proximate and distal bulkheads thereby in effect providing a second spar.
  • the proximate region of the first moulding projects beyond the proximate bulkhead, each of the proximate and distal bulkheads and the rear edge upstands of the third moulding underlie the top of the second moulding; and the first moulding is bonded to the forward most surface of the web and the proximate and distal bulkheads as well as directly to the under surface of the top and the top surface of the bottom of said second moulding.
  • the assembly is ribless or at least substantially ribless.
  • said third moulding is pan like.
  • said second moulding defines the leading edge save near the distal region.
  • the present invention in an aspect is also comprises in combination, two or more mouldings for an assembly as previously defined.
  • the invention is a wing skin moulding having proximal and distal regions and for use in a wing assembly, said moulding providing a front, top and bottom exterior surface to define respectively the leading edge, the fore and rear regions of the upper surface and the fore region of the under surface of the wing assembly.
  • said moulding does not define the distal region of the leading edge.
  • a wing skin moulding is substantially herein described with reference to any one or more of the accompanying drawings.
  • the invention is an aircraft being an assembly of components of composite material, the components being or including: a fuselage right side, a fuselage left side bonded to said right side, a wing support moulding or component ("moulding") bonded to both of said sides and supporting a leading edge and top surface of stub wings in part defined by each side, the wing support moulding having a pan form with an upstanding perimeter, a right wing leading edge, top surface and front of bottom surface moulding or component (“moulding”), a left wing leading edge, top surface and front of bottom surface moulding or component
  • mouldings Preferably at least a majority of said mouldings are one-shot mouldings.
  • wing support moulding transits under the cockpit opening defined by the mated fuselage side mouldings.
  • each wing foil is or can be ribless save for bulkheads (proximate and distal) provided by the upstanding perimeter of the wing rear et al mouldings.
  • the spars are channels that taper from their proximate region.
  • the invention is a method of wing assembly manufacture which involves the assembly of one-shot mouldings to provide a wing assembly as previously defined.
  • a wing assembly of at least three mouldings defining respectively : a first one shot moulding that provides an elongate spar of the wing assembly, a second one shot moulding which provides a front, top and bottom thereby to define respectively the leading edge (save optionally near the distal region), the fore and rear regions of the upper surface and the fore region of the under surface, and a third one shot moulding (preferably pan-like) providing a web bounded proximally, distally and rearwardly with upstands from the web thereby defining the rear under surface, a proximate bulkhead, a distal bulkhead and the rear edge, the rear edge upstanding from the web and extending between the proximate and distal bulkheads providing a second spar, wherein in the bonded wing assembly the proximate region
  • the invention is an aircraft having multiple one-shot mouldings of composite material, the mouldings being or including: a fuselage right side, a fuselage left side bonded to said right side, a wing support moulding bonded to both of said sides and supporting a leading edge and top surface of stub wings in part defined by each side, the wing support moulding having a pan form with an upstanding perimeter, a right wing leading edge, top surface and front of bottom surface moulding, a left wing leading edge, top surface and front of bottom surface moulding, a right wing spar leading edge, top surface and front of bottom surface moulding, a left wing spar leading edge, top surface and front of bottom surface moulding, a right wing rear under surface moulding having a pan form with an upstanding perimeter, a left wing rear under surface moulding having a pan form with an upstanding perimeter, wherein each spar at its proximate end bonds to at least the wing support moulding and at its further out region(s) to each of its two wing mould
  • the invention is an aircraft fuselage having or being (at least primarily) of: a one-shot moulded right side of a composite material and providing at least part of the exterior surface of a right wing stub, a one-shot moulded left side of a composite material and providing at least part of the exterior surface of a left wing stub, the right and left half has been bonded to each other, and a one-shot moulded sparred component of a composite material located transversely through the joined right and left sides and bond attached to at least part of the right and left sides.
  • the right and left sides can be of a mirror image one of the other.
  • Such a web can include openings or gaps.
  • each side includes part of a bulkhead to be positioned as the rear of the cockpit space.
  • a preferred wing form (ignoring control surfaces and any wing tip structures or structure) is essentially an assembly of a three single shot mouldings.
  • the wing save for component provided bulkheads as partial ribs, is ribless.
  • Figure 5 shows the sub assembly of Figure 4 with the pan-like spar including form shown in Figure 4 bonded to the top side leading edge and fore region of stub wings and other parts of the fuselage,
  • Figure 7 is an exploded view of the three one shot component mouldings A, B and C embodied in the assembly of Figure 6 as well as the wing tip moulding or sub assembly D,
  • Figure 8 is a plan view showing a bolted right wing attachment to the fore spar of the pan- like fuselage component
  • Figure 9 is a frontal perspective view of the association of Figure 8.
  • the members co-act in the assembled form, as shown in Figure 6, to enclose a cavity between the members A, B and C. This can be used for a number of functions including, if desired, a fuel bladder.
  • trailing edge upstand 27 which acts as a secondary central wing spar.
  • test aircraft is merely one of a multiple of aircraft types that can benefit from the inventive aspects of the present invention.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Moulding By Coating Moulds (AREA)

Abstract

L'invention concerne un aéronef avec (I) un ensemble d'aile principal constitué de trois moulages, l'un fournissant un longeron, un deuxième la plus grande partie de l'extérieur y compris le bord d'attaque, et un troisième au moins la plus grande partie de l'intrados arrière et (II) un fuselage compatible. L'ensemble d'aile et ses composants constituent également l'invention.
PCT/NZ2008/000065 2007-03-29 2008-03-27 Fabrication et assemblage de composant d'aéronef Ceased WO2008121005A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NZ55425507 2007-03-29
NZ554255 2007-03-29

Publications (1)

Publication Number Publication Date
WO2008121005A1 true WO2008121005A1 (fr) 2008-10-09

Family

ID=39808500

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NZ2008/000065 Ceased WO2008121005A1 (fr) 2007-03-29 2008-03-27 Fabrication et assemblage de composant d'aéronef

Country Status (1)

Country Link
WO (1) WO2008121005A1 (fr)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012004490A1 (fr) * 2010-07-09 2012-01-12 Airbus Operations Sas Procede de realisation d'un caisson central de voilure
WO2012169906A1 (fr) 2011-06-07 2012-12-13 Composite Helicopter Holdings Limited Hélicoptère
EP2741957A4 (fr) * 2011-08-09 2015-08-19 Abe Karem Aéronef à multiples rôles ayant des modules de mission interchangeables
US9221532B2 (en) 2010-08-12 2015-12-29 Abe Karem Multi-role aircraft with interchangeable mission modules
EP3272646A1 (fr) * 2016-07-20 2018-01-24 Airbus Operations, S.L. Structure de pointe injectée moulée thermoplastique pour un avion
EP3335982A1 (fr) * 2016-12-16 2018-06-20 Airbus Operations, S.L. Aéronef ayant une section arrière comprenant un revêtement continu pour le fuselage et l'empennage vertical
EP3498592A1 (fr) 2017-12-13 2019-06-19 FLARIS Spolka z ograniczona odpowiedzialnoscia Structure de jonction métal/composite pour un avion
US10486791B2 (en) * 2016-12-02 2019-11-26 Airbus Operations Limited Aerofoil structure components

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1808842A (en) * 1930-08-18 1931-06-09 Fedor John Paul Aeroplane wing
US2560742A (en) * 1949-01-29 1951-07-17 Monogram Models Inc Wing construction for model airplanes
US4739954A (en) * 1986-12-29 1988-04-26 Hamilton Terry W Over-lap rib joint
US6116539A (en) * 1999-03-19 2000-09-12 Williams International Co. L.L.C. Aeroelastically stable forward swept wing
US20030192990A1 (en) * 1999-11-18 2003-10-16 Simpson Craig B. Single piece co-cure composite wing
FR2846939A1 (fr) * 2002-11-13 2004-05-14 Soc D Const Aeronautique Auver Procede de fabrication d'une aile d'avion leger

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1808842A (en) * 1930-08-18 1931-06-09 Fedor John Paul Aeroplane wing
US2560742A (en) * 1949-01-29 1951-07-17 Monogram Models Inc Wing construction for model airplanes
US4739954A (en) * 1986-12-29 1988-04-26 Hamilton Terry W Over-lap rib joint
US6116539A (en) * 1999-03-19 2000-09-12 Williams International Co. L.L.C. Aeroelastically stable forward swept wing
US20030192990A1 (en) * 1999-11-18 2003-10-16 Simpson Craig B. Single piece co-cure composite wing
FR2846939A1 (fr) * 2002-11-13 2004-05-14 Soc D Const Aeronautique Auver Procede de fabrication d'une aile d'avion leger

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2962409A1 (fr) * 2010-07-09 2012-01-13 Airbus Operations Sas Procede de realisation d'un caisson central de voilure
CN103003146A (zh) * 2010-07-09 2013-03-27 空中客车运营简化股份公司 制造中心翼盒的方法
WO2012004490A1 (fr) * 2010-07-09 2012-01-12 Airbus Operations Sas Procede de realisation d'un caisson central de voilure
CN103003146B (zh) * 2010-07-09 2016-08-24 空中客车运营简化股份公司 制造中心翼盒的方法
US9114582B2 (en) 2010-07-09 2015-08-25 Airbus Operations Sas Method for producing a central wing box
US9221532B2 (en) 2010-08-12 2015-12-29 Abe Karem Multi-role aircraft with interchangeable mission modules
US9493226B2 (en) 2010-08-12 2016-11-15 Abe Karem Multi-role aircraft with interchangeable mission modules
EP2718180A4 (fr) * 2011-06-07 2015-07-22 Composite Helicopters Internat Holdings Ltd Hélicoptère
WO2012169906A1 (fr) 2011-06-07 2012-12-13 Composite Helicopter Holdings Limited Hélicoptère
US9932123B2 (en) 2011-06-07 2018-04-03 Composite Helicopters International Holdings Ltd Monocoque helicopter fuselage with integral tail boom
EP2741957A4 (fr) * 2011-08-09 2015-08-19 Abe Karem Aéronef à multiples rôles ayant des modules de mission interchangeables
EP3272646A1 (fr) * 2016-07-20 2018-01-24 Airbus Operations, S.L. Structure de pointe injectée moulée thermoplastique pour un avion
US20180022438A1 (en) * 2016-07-20 2018-01-25 Airbus Operations, S.L. Thermoplastic moulded injected tip structure for an aircraft
US10745105B2 (en) 2016-07-20 2020-08-18 Airbus Operations, S.L. Thermoplastic moulded injected tip structure for an aircraft
US10486791B2 (en) * 2016-12-02 2019-11-26 Airbus Operations Limited Aerofoil structure components
EP3335982A1 (fr) * 2016-12-16 2018-06-20 Airbus Operations, S.L. Aéronef ayant une section arrière comprenant un revêtement continu pour le fuselage et l'empennage vertical
CN108202857A (zh) * 2016-12-16 2018-06-26 空中客车西班牙运营有限责任公司 包括具有用于机身和竖向尾翼的连续蒙皮的后部部段的飞行器
CN108202857B (zh) * 2016-12-16 2022-10-04 空中客车西班牙运营有限责任公司 包括具有用于机身和竖向尾翼的连续蒙皮的后部部段的飞行器
EP3498592A1 (fr) 2017-12-13 2019-06-19 FLARIS Spolka z ograniczona odpowiedzialnoscia Structure de jonction métal/composite pour un avion

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