WO2005087589A1 - Stratifie avec elements chauffants - Google Patents

Stratifie avec elements chauffants Download PDF

Info

Publication number
WO2005087589A1
WO2005087589A1 PCT/NL2005/000201 NL2005000201W WO2005087589A1 WO 2005087589 A1 WO2005087589 A1 WO 2005087589A1 NL 2005000201 W NL2005000201 W NL 2005000201W WO 2005087589 A1 WO2005087589 A1 WO 2005087589A1
Authority
WO
WIPO (PCT)
Prior art keywords
layer
laminate according
layers
metal layers
heating layer
Prior art date
Application number
PCT/NL2005/000201
Other languages
English (en)
Inventor
Leonardus Johannes Bernard Peeters
Original Assignee
Stork Fokker Aesp B.V.
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 Stork Fokker Aesp B.V. filed Critical Stork Fokker Aesp B.V.
Publication of WO2005087589A1 publication Critical patent/WO2005087589A1/fr

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
    • B32B7/04—Interconnection of layers
    • B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
    • B32B15/08—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin
    • B32B15/092—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material of synthetic resin comprising epoxy resins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B15/00—Layered products comprising a layer of metal
    • B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B17/00—Layered products essentially comprising sheet glass, or glass, slag, or like fibres
    • B32B17/02—Layered products essentially comprising sheet glass, or glass, slag, or like fibres in the form of fibres or filaments
    • B32B17/04—Layered products essentially comprising sheet glass, or glass, slag, or like fibres in the form of fibres or filaments bonded with or embedded in a plastic substance
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
    • B64D15/12—De-icing or preventing icing on exterior surfaces of aircraft by electric heating
    • H—ELECTRICITY
    • H05—ELECTRIC TECHNIQUES NOT OTHERWISE PROVIDED FOR
    • H05B—ELECTRIC HEATING; ELECTRIC LIGHT SOURCES NOT OTHERWISE PROVIDED FOR; CIRCUIT ARRANGEMENTS FOR ELECTRIC LIGHT SOURCES, IN GENERAL
    • H05B3/00—Ohmic-resistance heating
    • H05B3/20—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater
    • H05B3/22—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater non-flexible
    • H05B3/28—Heating elements having extended surface area substantially in a two-dimensional plane, e.g. plate-heater non-flexible heating conductor embedded in insulating material
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/20—Properties of the layers or laminate having particular electrical or magnetic properties, e.g. piezoelectric
    • B32B2307/206—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2307/00—Properties of the layers or laminate
    • B32B2307/30—Properties of the layers or laminate having particular thermal properties
    • B32B2307/304—Insulating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2311/00—Metals, their alloys or their compounds
    • B32B2311/24—Aluminium
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B32—LAYERED PRODUCTS
    • B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
    • B32B2363/00—Epoxy resins
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0233—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes comprising de-icing means

Definitions

  • the invention relates to a laminate consisting of alternating metal layers and plastic adhesive layers located between the metal layers for the production of structural parts such as panels that can be used in aviation and/or aerospace.
  • Such laminates are known and are used in panels for various components of the load-bearing aircraft construction. Examples are the skin panels for the aircraft body and the wing panels for the aircraft wings.
  • Panels that consist of a laminate have substantial advantages compared with completely metal panels, such as aluminium panels.
  • the weight of panels consisting of a laminate having otherwise equal strength and rigidity is lower than that of panels consisting wholly of aluminium.
  • the fatigue characteristics of such laminates are much more advantageous. Any cracks in the metal layers are stopped by the adjacent plastic layers, such that no further crack growth will occur even under fluctuating loads.
  • Another advantage of such laminates lies in the good ability to withstand collisions. This characteristic is particularly important in the case of use in the leading edges of the wings and the tail and of the skin panels of moving wing and tail components.
  • the problem of icing can arise with certain panels of the aircraft construction.
  • ice growth at the leading edge of the wing is dangerous.
  • Such ice growth influences the flow of air over the wing, such that the load bearing capacity of the wing can decrease sharply.
  • the leading edge of the wings is frequently provided with anti-icing means. These can both prevent the formation of ice and also contribute to the removal of ice that has already grown.
  • panels that consist of laminates it is known to glue a heatable film on the leading edge.
  • the aim of the invention is, therefore, to provide a laminate that has a high structural rigidity and strength in combination with good collision or impact characteristics and that is provided with heating means that are protected against environmental influences. Said aim is achieved in that an electrical heating layer is provided between at least two metal layers, which heating layer is electrically insulated with respect to said metal layers.
  • the laminate according to the invention consists of alternating metal layers and plastic layers and consequently has good mechanical properties. Electrical heating means are also embedded in the interior of the laminate, preferably as close as possible to the outer layer. Electrical insulation of the heating means with respect to the adjacent metal layers can be obtained by means of two electrically insulating layers. These electrically insulating layers can also be the plastic adhesive layers, which, after all, already form part of the standard laminate.
  • a layer with thermal barrier characteristics for example, consisting of glass or epoxy, can be on the inside of the heatable layer.
  • the heating energy can consequently be directed mainly at the outer metal layer where icing can occur.
  • the heating layer can be implemented in various ways. According to a first possibility, this can comprise a resistance foil. According to an alternative embodiment, the heating layer can comprise a woven layer in which there are resistance wires.
  • the laminate can also be constructed in various ways, for example with plastic adhesive layers which each comprise at least one fibre-reinforced layer (FML), or with plastic adhesive layers which each comprise at least one layer of adhesive (AML).
  • the fibre-reinforced layers can comprise polymer fibres or ceramic fibres such as glass.
  • the layer of adhesive can comprise epoxy, PUR, PE, PEI or PMMA.
  • the heating layer can contain a heating element that is incorporated in such a layer of adhesive.
  • the metal layers preferably comprise aluminium, the thickness of which can be between, or can be equal to, 0.3 and 0.5 mm.
  • the thickness of the plastic layers can be between, or equal to, 0.1 and 0.3 mm.
  • the invention also relates to an external component for an aircraft or spacecraft.
  • the component concerned can be, for example, the leading edge for a wing or for the tail piece of an aircraft.
  • the invention also relates to components such as an inlet piece for a motor or an air feed. All such components are found in those regions of an aircraft or spacecraft that are directly exposed to air flows impinging thereon and that therefore are susceptible to icing. According to the invention, such components are provided with the laminate according to the invention.
  • the laminate can also be applied to a support consisting of a relatively thick sheet metal, such as aluminium.
  • the invention relates to the use of the laminate as described above for such an external component of an aircraft or spacecraft. It will be clear that many different conceivable variants in the stacking of the various layers are conceivable. That is to say metal layers, layers of adhesive, electrically insulating layers and heating layers.
  • M metal layer
  • E electrically insulating layer
  • a layer of adhesive T layer with thermal barrier characteristics, which optionally can comprise an adhesive
  • the examples can be represented as follows (the heating layer always being close to the outside): 1.
  • MFFMFFMFFEWEM M K M K M K W E M 5.
  • Figure 1 shows a section through the leading edge of a wing.
  • Figure 2 shows detail II from Figure 1 on an enlarged scale.
  • the leading edge of a wing which is indicated in its entirety by 10, is shown in cross-section.
  • the leading edge of a wing adjoins two panels 11,12 and is fixed thereto by means of fixing means known per se, which are not shown in more detail.
  • the leading edge of the wing consists of a curved laminate that is shown in section on a larger scale in Figure 2.
  • the laminate comprises metal layers, in particular aluminium layers 1, as well as plastic adhesive layers 2 located between the metal layers.
  • these plastic adhesive layers consist of fibre-reinforced plastic layers 3, 4, which are oriented at 90° with respect to one another (prepreg).
  • This can be, for example, an aluminium resistance foil, a woven layer with resistance wires incorporated therein, etc.
  • an electrical insulation layer 8 which, for example, can also be a fibre-reinforced plastic adhesive layer, between the heating layer 7 and the outer aluminium layer 1.
  • an insulation layer 9 can be provided on the inside of the heating layer 7.
  • a supplementary thermal insulation layer 9 is that the heat mainly reaches the outer aluminium layer 1, which is susceptible to icing.

Abstract

Un stratifié est constitué de couches de métal alternantes et de couches adhésives plastiques disposées entre les couches de métal; ce stratifié sert à la production de pièces structurelles tels que des panneaux qui peuvent s'utiliser en industries aéronautique et/ou aérospatiale. Il est caractérisé en ce qu'une couche électrique chauffante est ménagée entre au moins deux couches de métal, ladite couche chauffante étant isolée électriquement par rapport aux couches métalliques. La couche chauffante est incorporée entre deux couches électriquement isolantes.
PCT/NL2005/000201 2004-03-16 2005-03-16 Stratifie avec elements chauffants WO2005087589A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
NL1025744 2004-03-16
NL1025744A NL1025744C2 (nl) 2004-03-16 2004-03-16 Laminaat met verwarmingselement.

Publications (1)

Publication Number Publication Date
WO2005087589A1 true WO2005087589A1 (fr) 2005-09-22

Family

ID=32822970

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/NL2005/000201 WO2005087589A1 (fr) 2004-03-16 2005-03-16 Stratifie avec elements chauffants

Country Status (2)

Country Link
NL (1) NL1025744C2 (fr)
WO (1) WO2005087589A1 (fr)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007071398A1 (fr) * 2005-12-20 2007-06-28 Airbus Deutschland Gmbh Dispositif de protection
FR2898868A1 (fr) * 2006-03-24 2007-09-28 Aircelle Sa Structure pour levre d'entree d'air de nacelle a degivrage electrique
WO2010074942A1 (fr) 2008-12-24 2010-07-01 Mra Systems, Inc. Système antigivrage et procédé permettant de prévenir l'accumulation de glace
WO2011157953A1 (fr) * 2010-06-18 2011-12-22 Snecma Manche d'entree d'air pour nacelle de turboreacteur
EP2591476A2 (fr) * 2010-07-11 2013-05-15 Advanced Logistics Development Ltd. Matériau composite, élément de construction constitué du matériau composite, longeron d'aile d'avion et leurs procédés de production
US9267715B2 (en) 2012-02-03 2016-02-23 Airbus Operations Gmbh Icing protection system for an aircraft and method for operating an icing protection system
EP3006189A1 (fr) * 2014-10-09 2016-04-13 The Boeing Company Structures composites à joints composite et métal et leurs procédés de fabrication
US9522512B2 (en) 2010-08-17 2016-12-20 The Boeing Company Methods for making composite structures having composite-to-metal joints
US10112373B2 (en) 2010-08-17 2018-10-30 The Boeing Company Multi-layer metallic structure and composite-to-metal joint methods
US11952130B2 (en) 2020-03-27 2024-04-09 Airbus Operations Gmbh Structural component for an aircraft with integrated heating layer and structural battery

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1230668A (fr) * 1958-04-24 1960-09-19 Goodrich Co B F Procédé et appareillage pour la fabrication des stratifiés chauffants, applicables notamment aux éléments de dégivrage d'avions
FR1428560A (fr) * 1965-01-04 1966-02-18 Nouvelle plaque chauffante stratifiée
EP0459216A2 (fr) * 1990-06-01 1991-12-04 The B.F. Goodrich Company Dégivreur à résistance électrique
US5951800A (en) * 1992-11-18 1999-09-14 Mcdonnell Douglas Corp. Fiber/metal laminate splice
WO2001008463A2 (fr) 1999-07-30 2001-02-08 Northcoast Technologies Dispositif de degivrage pour aeronef
WO2001017850A1 (fr) * 1999-09-10 2001-03-15 Bfgoodrich Company Panneau de sol chauffant pour avion
WO2002094565A1 (fr) * 2001-05-21 2002-11-28 Fokker Aerostructures B.V. Procede de fabrication d'un stratifie façonne
WO2003038841A1 (fr) 2001-10-17 2003-05-08 Rung-Rannow Joerg Film chauffant constitue de plusieurs couches et procede de production de ce film

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1230668A (fr) * 1958-04-24 1960-09-19 Goodrich Co B F Procédé et appareillage pour la fabrication des stratifiés chauffants, applicables notamment aux éléments de dégivrage d'avions
FR1428560A (fr) * 1965-01-04 1966-02-18 Nouvelle plaque chauffante stratifiée
EP0459216A2 (fr) * 1990-06-01 1991-12-04 The B.F. Goodrich Company Dégivreur à résistance électrique
US5951800A (en) * 1992-11-18 1999-09-14 Mcdonnell Douglas Corp. Fiber/metal laminate splice
WO2001008463A2 (fr) 1999-07-30 2001-02-08 Northcoast Technologies Dispositif de degivrage pour aeronef
WO2001017850A1 (fr) * 1999-09-10 2001-03-15 Bfgoodrich Company Panneau de sol chauffant pour avion
WO2002094565A1 (fr) * 2001-05-21 2002-11-28 Fokker Aerostructures B.V. Procede de fabrication d'un stratifie façonne
WO2003038841A1 (fr) 2001-10-17 2003-05-08 Rung-Rannow Joerg Film chauffant constitue de plusieurs couches et procede de production de ce film

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007071398A1 (fr) * 2005-12-20 2007-06-28 Airbus Deutschland Gmbh Dispositif de protection
FR2898868A1 (fr) * 2006-03-24 2007-09-28 Aircelle Sa Structure pour levre d'entree d'air de nacelle a degivrage electrique
WO2007110494A1 (fr) * 2006-03-24 2007-10-04 Aircelle Structure pour levre d’entree d’air de nacelle a degivrage electrique comprenant une zone d’attenuation acoustique
US8240982B2 (en) 2006-03-24 2012-08-14 Aircelle Structure for an air inlet lip of an electric de-icing pod comprising an acoustic attenuation zone
WO2010074942A1 (fr) 2008-12-24 2010-07-01 Mra Systems, Inc. Système antigivrage et procédé permettant de prévenir l'accumulation de glace
JP2012513934A (ja) * 2008-12-24 2012-06-21 エムアールエイ・システムズ・インコーポレイテッド 氷の蓄積を防ぐ防氷システムおよび方法
US9004407B2 (en) 2008-12-24 2015-04-14 Middle River Aircraft Systems Anti-icing system and method for preventing ice accumulation
US9006119B2 (en) 2009-10-01 2015-04-14 A.L.D. Advanced Logistics Development Ltd. Composite material, a structural element comprised of the composite material, an airplane wing spar and their methods of production
WO2011157953A1 (fr) * 2010-06-18 2011-12-22 Snecma Manche d'entree d'air pour nacelle de turboreacteur
FR2961484A1 (fr) * 2010-06-18 2011-12-23 Snecma Manche d’entree d’air pour nacelle de turboreacteur
GB2494843A (en) * 2010-06-18 2013-03-20 Snecma Air inlet duct for a turbojet nacelle
EP2591476A4 (fr) * 2010-07-11 2014-11-19 Advanced Logistics Dev Ltd Matériau composite, élément de construction constitué du matériau composite, longeron d'aile d'avion et leurs procédés de production
EP2591476A2 (fr) * 2010-07-11 2013-05-15 Advanced Logistics Development Ltd. Matériau composite, élément de construction constitué du matériau composite, longeron d'aile d'avion et leurs procédés de production
US9522512B2 (en) 2010-08-17 2016-12-20 The Boeing Company Methods for making composite structures having composite-to-metal joints
US9919507B2 (en) 2010-08-17 2018-03-20 The Boeing Company Process for inhibiting galvanic corrosion of an aluminum structure connected, without using a splice plate, to a composite structure having a fiber including graphite
US10112373B2 (en) 2010-08-17 2018-10-30 The Boeing Company Multi-layer metallic structure and composite-to-metal joint methods
US11084269B2 (en) 2010-08-17 2021-08-10 The Boeing Company Multi-layer metallic structure and composite-to-metal joint methods
US9267715B2 (en) 2012-02-03 2016-02-23 Airbus Operations Gmbh Icing protection system for an aircraft and method for operating an icing protection system
EP3006189A1 (fr) * 2014-10-09 2016-04-13 The Boeing Company Structures composites à joints composite et métal et leurs procédés de fabrication
CN105501428A (zh) * 2014-10-09 2016-04-20 波音公司 具有复合物-金属接头的复合结构及其制造方法
CN105501428B (zh) * 2014-10-09 2020-06-30 波音公司 具有复合物-金属接头的复合结构及其制造方法
US11952130B2 (en) 2020-03-27 2024-04-09 Airbus Operations Gmbh Structural component for an aircraft with integrated heating layer and structural battery

Also Published As

Publication number Publication date
NL1025744A1 (nl) 2004-05-27
NL1025744C2 (nl) 2005-01-18

Similar Documents

Publication Publication Date Title
WO2005087589A1 (fr) Stratifie avec elements chauffants
US9751612B2 (en) Multifunctional composite material including a viscoelastic interlayer
EP3339013B1 (fr) Panneaux de plancher avec tissu d'isolation électrique et thermiquement conducteur
EP2523854B1 (fr) Système de dégivrage/antigivrage multifonctionnel
EP3297395B1 (fr) Couche de protection isolante électriquement et thermiquement conductrice pour chauffages de dégivrage
US11597524B2 (en) Heating device and method for manufacturing same
US10343372B2 (en) Composite article having multifunctional properties and method for its manufacture
US11338933B2 (en) Acoustic honeycomb panel with integrated electrical heater
US10960966B2 (en) Cabin structural component, method for producing a cabin structural component, cabin assembly and transport vehicle
US20120292439A1 (en) Article with de-icing/anti-icing function
US11130559B2 (en) Heated panels with ballistic structures
EP3342702B1 (fr) Bande d'érosion intégrée à des éléments de dégivrage/anti-givrage à base d'allotrope de carbone
JP2000356358A (ja) 特に航空機内の床面プレート用のプレート構成部材
US11040765B2 (en) Advanced composite heated floor panel
CN103569364A (zh) 用于集成到飞机隔音板中的电加热器
EP3592106B1 (fr) Panneaux de plancher chauffants
US20130122245A1 (en) Embedded conductor honeycomb core and sandwich panel incorporating same
EP3407678A1 (fr) Procédé de fabrication de feuilles de nanotube carbone complexes
CA3040698A1 (fr) Composante structurelle d'un aeronef
EP3297394B1 (fr) Couche de protection de tissu à nanofibres d'alumine pour dégivreuses
US9072184B2 (en) Carbon fiber spacecraft panel with integral metallic foil power return
EP4108572B1 (fr) Caractéristique d'aéronef avec système de chauffage formé de graphène induit par laser
EP3725669A1 (fr) Panneaux composites chauffés et non chauffés résistant aux dommages de bord et dotés de pièces de bord rotatives en nid d'abeille
EP2746161B1 (fr) Structure d'aéronef résistant à la foudre et procédé de rééquipement d'une structure
CN114056544A (zh) 用于机翼的蒙皮结构，具有蒙皮结构的飞机和蒙皮结构的安装方法

Legal Events

Date Code Title Description
AK Designated states

Kind code of ref document: A1

Designated state(s): AE AG AL AM AT AU AZ BA BB BG BR BW BY BZ CA CH CN CO CR CU CZ DE DK DM DZ EC EE EG ES FI GB GD GE GH GM HR HU ID IL IN IS JP KE KG KP KR KZ LC LK LR LS LT LU LV MA MD MG MK MN MW MX MZ NA NI NO NZ OM PG PH PL PT RO RU SC SD SE SG SK SL SM SY TJ TM TN TR TT TZ UA UG US UZ VC VN YU ZA ZM ZW

AL Designated countries for regional patents

Kind code of ref document: A1

Designated state(s): BW GH GM KE LS MW MZ NA SD SL SZ TZ UG ZM ZW AM AZ BY KG KZ MD RU TJ TM AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LT LU MC NL PL PT RO SE SI SK TR BF BJ CF CG CI CM GA GN GQ GW ML MR NE SN TD TG

121 Ep: the epo has been informed by wipo that ep was designated in this application
DPEN Request for preliminary examination filed prior to expiration of 19th month from priority date (pct application filed from 20040101)
NENP Non-entry into the national phase

Ref country code: DE

WWW Wipo information: withdrawn in national office

Country of ref document: DE

122 Ep: pct application non-entry in european phase