WO2014198956A1 - Procédé et système d'antigivrage / dégivrage de porte d'aéronef et porte d'aéronef équipée d'un tel système - Google Patents
Procédé et système d'antigivrage / dégivrage de porte d'aéronef et porte d'aéronef équipée d'un tel système Download PDFInfo
- Publication number
- WO2014198956A1 WO2014198956A1 PCT/EP2014/062486 EP2014062486W WO2014198956A1 WO 2014198956 A1 WO2014198956 A1 WO 2014198956A1 EP 2014062486 W EP2014062486 W EP 2014062486W WO 2014198956 A1 WO2014198956 A1 WO 2014198956A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- icing
- door
- fuselage
- aircraft
- energy
- Prior art date
Links
- 230000005284 excitation Effects 0.000 claims abstract description 21
- 238000007789 sealing Methods 0.000 claims abstract description 6
- 239000004020 conductor Substances 0.000 claims description 15
- 238000000034 method Methods 0.000 claims description 12
- 238000009423 ventilation Methods 0.000 claims description 6
- 239000002131 composite material Substances 0.000 claims description 4
- 239000000463 material Substances 0.000 claims description 3
- 229910001092 metal group alloy Inorganic materials 0.000 claims description 3
- 239000002103 nanocoating Substances 0.000 claims description 3
- 239000003973 paint Substances 0.000 claims description 3
- 239000004593 Epoxy Substances 0.000 claims description 2
- 239000000806 elastomer Substances 0.000 claims description 2
- 229920001971 elastomer Polymers 0.000 claims description 2
- 239000012777 electrically insulating material Substances 0.000 claims description 2
- 239000000835 fiber Substances 0.000 claims description 2
- 239000002657 fibrous material Substances 0.000 claims description 2
- 230000001960 triggered effect Effects 0.000 claims description 2
- 238000002604 ultrasonography Methods 0.000 claims description 2
- 230000001681 protective effect Effects 0.000 claims 2
- 229920001296 polysiloxane Polymers 0.000 claims 1
- 230000015572 biosynthetic process Effects 0.000 abstract description 7
- 238000009432 framing Methods 0.000 abstract description 2
- 230000007246 mechanism Effects 0.000 description 5
- 238000010438 heat treatment Methods 0.000 description 4
- 229920000049 Carbon (fiber) Polymers 0.000 description 2
- 239000004917 carbon fiber Substances 0.000 description 2
- 239000000919 ceramic Substances 0.000 description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 230000002787 reinforcement Effects 0.000 description 2
- 230000035939 shock Effects 0.000 description 2
- 238000010257 thawing Methods 0.000 description 2
- BIIBYWQGRFWQKM-JVVROLKMSA-N (2S)-N-[4-(cyclopropylamino)-3,4-dioxo-1-[(3S)-2-oxopyrrolidin-3-yl]butan-2-yl]-2-[[(E)-3-(2,4-dichlorophenyl)prop-2-enoyl]amino]-4,4-dimethylpentanamide Chemical compound CC(C)(C)C[C@@H](C(NC(C[C@H](CCN1)C1=O)C(C(NC1CC1)=O)=O)=O)NC(/C=C/C(C=CC(Cl)=C1)=C1Cl)=O BIIBYWQGRFWQKM-JVVROLKMSA-N 0.000 description 1
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 1
- 229910045601 alloy Inorganic materials 0.000 description 1
- 239000000956 alloy Substances 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000008014 freezing Effects 0.000 description 1
- 238000007710 freezing Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000017525 heat dissipation Effects 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 230000002265 prevention Effects 0.000 description 1
- 230000001737 promoting effect Effects 0.000 description 1
- 239000002210 silicon-based material Substances 0.000 description 1
- 238000004513 sizing Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000009466 transformation Effects 0.000 description 1
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT 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
-
- 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
- B64C1/14—Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers
- B64C1/1407—Doors; surrounding frames
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D15/00—De-icing or preventing icing on exterior surfaces of aircraft
- B64D15/02—De-icing or preventing icing on exterior surfaces of aircraft by ducted hot gas or liquid
- B64D15/04—Hot gas application
-
- 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
- F16J—PISTONS; CYLINDERS; SEALINGS
- F16J15/00—Sealings
- F16J15/02—Sealings between relatively-stationary surfaces
- F16J15/06—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces
- F16J15/064—Sealings between relatively-stationary surfaces with solid packing compressed between sealing surfaces the packing combining the sealing function with other functions
Definitions
- the invention relates to a method and an aircraft door anti-icing / deicing system, and an aircraft door equipped with this system.
- the invention makes it possible, in general, to protect the door against frost or ice, either to prevent their formation or to make them disappear.
- the invention is to prevent the formation of ice or to facilitate the breaking of the ice in the case where said formation could not be prevented.
- ice also applies to frost, which arises from the transformation of liquid water into a thin layer of ice.
- the door opening mechanism consists of a lever arm capable of lifting the door before turning and breaking the ice by shear with a low flexural component during this lift.
- the lifting mechanism is dimensioned to meet the aircraft certification which imposes an easy break of a layer of ice up to 2 or 3 mm or more. This dimensioning of the opening mechanisms also requires reinforcements for these mechanisms to be sufficiently robust in order to generate significant forces on the door edges.
- the invention aims precisely to facilitate the opening of the aircraft doors by preventing the formation of ice or, at the very least, by promoting rapid breakage of the ice on the door edges in connection with the skin of the aircraft. fuselage. To do this, it is planned to bring energy along the door when special conditions are met.
- the present invention relates to a method of anti-icing / deicing an aircraft equipment having an opening to the outside of the aircraft framed by the fuselage via a seal in position closed, in particular an aircraft door, an outside door handle or a ventilation panel.
- This method consists of dissipating excitation energy along at least one area that follows at least part of the seal of the opening of the equipment, the dissipation being triggered when the engines of the aircraft are running and the outside temperature is less than or substantially equal to a reference temperature.
- the extent of dissipation of energy may be in the joint, in the joint support, which may form with the joint the same part, or near the joint, on the equipment or on the fuselage framing 'equipment.
- the excitation energy is dissipated on a door edge, in particular along at least one lateral face of the door, and / or along a lateral side of the fuselage parallel to said door edge;
- the excitation energy is chosen from thermal, vibratory, electro-expulsive and pneumatic energy; the thermal energy is implemented by an electric current;
- the pneumatic energy is implemented by a stream of hot air under pressure.
- the invention also relates to an equipment anti-icing / de-icing system, in particular a door, an outside door handle or a ventilation panel of an aircraft comprising including engines and a control center, this system being able to implement the above method.
- a system comprises a source of excitation energy, a management computer which receives temperature information and operating information of the engines of the control unit, and means for dissipating such energy are suitable for extending parallel to at least a portion of a seal of said equipment.
- the dissipation means are able to extend parallel to at least one lateral face of the aircraft door, along a joint support wall of sealing secured to the door facing a lateral fuselage side of the door frame and / or along this side fuselage side, the seal of the door being adapted to be pressed against a support coming from a side face of the fuselage when the door is closed.
- This system reduces the efforts and the door opening time in an emergency or standard, limiting or removing the present ice - or at least facilitating its break - in the rebate zone between the faces side.
- the gain in effort makes it possible to reduce the size of the door opening mechanisms, to lighten them and thus to reduce their cost.
- the means of dissipation of the excitation energy consist of at least one insulated electrical conductor which extends along the support wall of the seal and the source of excitation energy is a source of an electric voltage which transmits a current of suitable intensity suitable for heating the conductor to a temperature not exceeding a determined ceiling value, in order to avoid any risk of burns by contact with the surrounding walls;
- the support of the seal is made of a material chosen from epoxy carbon fibers, composite fiber materials, silicone-based materials and elastomers, and the conductor is formed of a metal alloy filament housed in the core of a sheath of electrically insulating material, the conductor being secured at least partially on or in said support;
- the means of dissipation of the excitation energy are constituted by ultrasound emitters and the energy source is an ultrasonic source;
- the means of dissipation of the excitation energy consist of loops of dissipation of an electro-repulsive energy produced by a source of electrical pulses;
- the dissipation means of the excitation energy consist of a jet of pressurized hot air supplied by a preheated air compressor as a source of energy;
- release layers are also deposited on the skin of the door and the fuselage near the junction frame between the door and the fuselage, in particular a nano-coating chemically bonded to said skins and / or an electrically conductive paint strip connected to a voltage source.
- the invention also relates to an aircraft door equipped with the anti-icing / deicing system defined above, as well as to an aircraft equipped with an anti-icing / deicing system of the type defined above, " of the type "meaning here that the system is no longer dedicated exclusively to the door but, mutatis mutandis, to another equipment provided with at least one seal.
- the system is then arranged near at least one seal of an equipment of the aircraft selected from doors, outside door handles and ventilation panels.
- FIGS. 2 and 2a a sectional view of the door / fuselage junction and an enlargement in an exemplary embodiment according to the invention
- lateral means in extension perpendicular to the median plane of the aircraft
- qualifiers of the "superior”, “vertical” or “horizontal” type refer to the positioning of elements. in standard mode of use.
- the aircraft is equipped with a central control engine and accessories in conjunction with a management computer that receives temperature information and operation of the engines of the control center.
- the aircraft is built around a fuselage in which access and evacuation doors are fitted out.
- the inner face 1 i of an aircraft door 1 is illustrated in the closed position and framed by the fuselage 2.
- the door 1 has a hinge arm 3 fit to pivot the door 1, when opened, parallel to itself along the outer skin of the fuselage 2, to open a passenger evacuation space limited by the frame made by a cutout 20 of the fuselage 2 .
- This frame consists of three substantially linear faces, two lateral faces 21 and 22 substantially vertical connected by an upper face 23 substantially horizontal.
- the frame cutout 20 is made opposite an edge 10 of the door 1 also having two substantially vertical faces 1 1 and 12 connected by a substantially horizontal face 13.
- the door 1 is equipped with an anti-icing / de-icing system comprising a source of excitation energy managed by the computer and means for dissipating such energy extending parallel to the edge 10 of the aircraft door 1.
- FIG. 2 A sectional view of the junction "J" between the face 1 1 of the door 1 and the frame face 21 of the fuselage 2 is illustrated with reference to Figure 2, according to an exemplary embodiment of the invention.
- a seal 4 held in a support 5 secured to the door 1 is pressurized against a support 6 formed on a side face 25 of the fuselage 2 when the door 1 is closed.
- the support 5 and the seal 4 are from the same molding and form a single piece.
- the support 5 extends along the face internal 1 i of the door 1, and on the side face 1 1 of the door 1 by a rim 50 said protection.
- This rim 50 protects the door against erosion, especially when it is made of composite material based on carbon fibers, erosion from the aerodynamic flow in flight. It also protects the door against shocks, for example repeated shocks of passengers' luggage.
- the support 5 is made of composite fibers and the source of excitation energy is a source of electrical voltage such as the source 60 which transmits a current of intensity between the ends of three filaments of electrical conductors 61, 62, 63.
- the intensity of the electric current is calibrated so that the temperature of the surrounding walls does not exceed a certain ceiling, for example 60 ° C, to avoid any risk of burns of a passenger or a passenger. operator by contact with one of these walls.
- the filaments 61 to 63 are metal alloy and are housed in sheaths 71 to 73 of plastic material to form insulated conductors 81 to 83 (see the enlargement of Figure 2a). These conductors are integrated in the rim 50 of the support 5 and extend parallel to the lateral face 51 of the support 5 which comes against the face 1 1 of the door 1.
- the side wall 51 faces the side wall 21 of the fuselage frame 2. Under these conditions, the ice formed between the outer skins 2 and 1 respectively of the fuselage 2 and the door 1 - with respect to the rebate zone between the lateral faces 1 1 and 21 of the junction "J" - disappears or at least is reduced by dissipation of the heat generated by the heated filaments 61 to 63.
- the sectional view of the junction "J 'between the door 1' and the fuselage 2 'of Figure 3 illustrates an alternative embodiment.
- two heat dissipation conductors 81 'and 82' similar to the conductors 81 and 82, are integrated in the frame 20 'of the fuselage 2' parallel to the lateral face 21 'of this fuselage 2'.
- the support 5 'of the gasket 4' has a thickness sufficient to accommodate the conductors 81 'and 82'.
- the seal 4 ' is deformed in pressure under the action of a knife 90 coming from a lateral face 25' of the fuselage 2 'in order to seal the door / fuselage connection.
- two pieces of nano-coating 7a and 7b forming non-stick layers are chemically related to the outer skin 1 e 'and 2e' respectively of the door 1 'and the fuselage 2'.
- the parts 7a and 7b are arranged near the junction J '.
- the presence of these coatings makes it possible to further facilitate the breakage or detachment of the ice formed on the outer skins 1 'and 2'.
- a strip of electrically conductive paint may be deposited to the outer skin 1 'and 2', near the junction J '. The ends of such a soundtrack connected to the terminals of a voltage source such as the source 60 ( Figure 2).
- the computer can trigger the system by energizing the filaments when the temperature data pass under a reference value, 10 ° C in the illustrated examples.
- the reference value may be between about 10 to 15 ° but could be greater than 15 ° or less than 10 ° depending on the weather conditions or the type of airline served.
- the thermal energy can be dissipated by an exothermic reaction between chemical components or by the combustion of a slow fuel.
- a de-icing solution - usually based on alcohol - is also sprayed along at least one door edge.
- the aircraft can be on the ground as well as in flight.
- the invention can also be applied in a similar manner to the seal of the outer handle of an aircraft door or to the joints of the ventilation panels.
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
- Materials Applied To Surfaces To Minimize Adherence Of Mist Or Water (AREA)
- Body Structure For Vehicles (AREA)
- Power-Operated Mechanisms For Wings (AREA)
Abstract
Description
Claims
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
BR112015031474-0A BR112015031474B1 (pt) | 2013-06-14 | 2014-06-14 | Método e sistema para anticongelação/descongelação de um equipamento de aeronave, e, porta de aeronaves e aeronave equipada com um sistema anticongelação/descongelação. |
EP14737168.6A EP3007921B1 (fr) | 2013-06-14 | 2014-06-14 | Procédé et système d'antigivrage / dégivrage de porte d'aéronef et porte d'aéronef équipée d'un tel système |
CA2915293A CA2915293C (fr) | 2013-06-14 | 2014-06-14 | Procede et systeme d'antigivrage/degivrage de porte d'aeronef et porte d'aeronef equipee d'un tel systeme |
US14/897,426 US10011363B2 (en) | 2013-06-14 | 2014-06-14 | Anti-icing / de-icing system for aircraft door and aircraft door equipped with such a system |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR1355589 | 2013-06-14 | ||
FR1355589A FR3006993B1 (fr) | 2013-06-14 | 2013-06-14 | Procede et systeme d'antigivrage / degivrage de porte d'aeronef et porte d'aeronef equipee d'un tel systeme |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2014198956A1 true WO2014198956A1 (fr) | 2014-12-18 |
Family
ID=49274801
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2014/062486 WO2014198956A1 (fr) | 2013-06-14 | 2014-06-14 | Procédé et système d'antigivrage / dégivrage de porte d'aéronef et porte d'aéronef équipée d'un tel système |
Country Status (6)
Country | Link |
---|---|
US (1) | US10011363B2 (fr) |
EP (1) | EP3007921B1 (fr) |
BR (1) | BR112015031474B1 (fr) |
CA (1) | CA2915293C (fr) |
FR (1) | FR3006993B1 (fr) |
WO (1) | WO2014198956A1 (fr) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2017029180A1 (fr) * | 2015-08-14 | 2017-02-23 | Airbus Operations Gmbh | Ensemble porte d'aéronef muni d'espace creux à bruit réduit pouvant être recouvert par une porte d'aéronef |
FR3050507A1 (fr) * | 2016-04-20 | 2017-10-27 | Sealicone | Joint composite pour ouvrant ou partie mobile d'aeronef comprenant au moins un polymere hydrofuge- procede de fabrication dudit joint |
Families Citing this family (9)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR3004423B1 (fr) * | 2013-04-12 | 2015-05-01 | Latecoere | Procede et systeme de visualisation de l'environnement externe d'un avion, ainsi que porte d'avion equipee d'un tel systeme |
US10215281B2 (en) * | 2016-05-04 | 2019-02-26 | The Boeing Company | Seal assembly for sealing relatively movable components |
FR3053023B1 (fr) * | 2016-06-22 | 2018-06-15 | Airbus Operations | Aeronef comprenant un espacement entre une ouverture et une porte qui comporte un bord amont avec une arete vive |
US10890022B2 (en) | 2018-10-10 | 2021-01-12 | Ford Global Technologies, Llc. | Ice-breaking hinge assemblies for vehicle closure members |
DE102018127024B3 (de) * | 2018-10-30 | 2019-10-31 | Airbus Operations Gmbh | Flugzeugtürdichtungssystem und Flugzeugtüranordnung |
EP3716728B1 (fr) * | 2019-03-27 | 2022-09-28 | Ningbo Geely Automobile Research & Development Co., Ltd. | Système de chauffage d'élément du battnat de véhicule |
CN111907692A (zh) * | 2020-08-14 | 2020-11-10 | 中国航空工业集团公司沈阳飞机设计研究所 | 一种舱门热密封结构 |
CN112591071B (zh) * | 2020-12-17 | 2022-03-15 | 中航沈飞民用飞机有限责任公司 | 一种舱门提升开启破冰机构 |
US20230124999A1 (en) * | 2021-10-14 | 2023-04-20 | Goodrich Corporation | Aircraft heating system for thermally disadvantaged zones |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0516526A1 (fr) * | 1991-05-30 | 1992-12-02 | Automobiles Peugeot | Dispositif d'étanchéité pour élément ouvrant de véhicule automobiles |
DE19942038C1 (de) * | 1999-09-03 | 2000-10-05 | Webasto Dachsysteme Gmbh | Deckel eines öffnungsfähigen Fahrzeugdachs mit in seinen Kunststoffrahmen eingebettetem Heizelement |
EP1541467A1 (fr) * | 2003-12-12 | 2005-06-15 | Eurocopter | Dispositif de dégivrage/antigivrage modulaire d'une surface aérodynamique |
US7775481B2 (en) | 2004-04-24 | 2010-08-17 | Esw Gmbh | Device for heating lock elements in aircraft |
US7900870B2 (en) | 2007-05-09 | 2011-03-08 | B/E Aerospace, Inc. | Vent door system with lever mechanism |
Family Cites Families (4)
Publication number | Priority date | Publication date | Assignee | Title |
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DE3500436A1 (de) * | 1984-02-01 | 1985-08-14 | VEB Fahrzeugzubehörwerke Ronneburg, DDR 6506 Ronneburg, Gera | Heizbare randzone bei dachausschnitten von fahrzeugen, insbesondere fuer den dichtungsbereich von glasklappdaechern |
US6266925B1 (en) * | 1998-07-15 | 2001-07-31 | Bard E. Camerer | Weather stripping system with heating element for vehicles |
FR2941439B1 (fr) * | 2009-01-28 | 2011-01-14 | Aircelle Sa | Dispositif de degivrage electrique et systeme de controle associe |
EP3031645A1 (fr) * | 2014-12-12 | 2016-06-15 | Continental Automotive GmbH | Joint d'étanchéité et dispositif de chauffage pour une fermeture de véhicule mobile |
-
2013
- 2013-06-14 FR FR1355589A patent/FR3006993B1/fr not_active Expired - Fee Related
-
2014
- 2014-06-14 WO PCT/EP2014/062486 patent/WO2014198956A1/fr active Application Filing
- 2014-06-14 CA CA2915293A patent/CA2915293C/fr active Active
- 2014-06-14 BR BR112015031474-0A patent/BR112015031474B1/pt active IP Right Grant
- 2014-06-14 US US14/897,426 patent/US10011363B2/en active Active
- 2014-06-14 EP EP14737168.6A patent/EP3007921B1/fr active Active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP0516526A1 (fr) * | 1991-05-30 | 1992-12-02 | Automobiles Peugeot | Dispositif d'étanchéité pour élément ouvrant de véhicule automobiles |
DE19942038C1 (de) * | 1999-09-03 | 2000-10-05 | Webasto Dachsysteme Gmbh | Deckel eines öffnungsfähigen Fahrzeugdachs mit in seinen Kunststoffrahmen eingebettetem Heizelement |
EP1541467A1 (fr) * | 2003-12-12 | 2005-06-15 | Eurocopter | Dispositif de dégivrage/antigivrage modulaire d'une surface aérodynamique |
US7775481B2 (en) | 2004-04-24 | 2010-08-17 | Esw Gmbh | Device for heating lock elements in aircraft |
US7900870B2 (en) | 2007-05-09 | 2011-03-08 | B/E Aerospace, Inc. | Vent door system with lever mechanism |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2017029180A1 (fr) * | 2015-08-14 | 2017-02-23 | Airbus Operations Gmbh | Ensemble porte d'aéronef muni d'espace creux à bruit réduit pouvant être recouvert par une porte d'aéronef |
CN107922044A (zh) * | 2015-08-14 | 2018-04-17 | 空中客车德国运营有限责任公司 | 具有可由飞行器门覆盖的降声空腔的飞行器门装置 |
US10882599B2 (en) | 2015-08-14 | 2021-01-05 | Airbus Operations Gmbh | Aircraft door arrangement with sound reduced hollow space which can be covered by an aircraft door |
CN107922044B (zh) * | 2015-08-14 | 2021-11-19 | 空中客车德国运营有限责任公司 | 具有可由飞行器门覆盖的降声空腔的飞行器门装置 |
FR3050507A1 (fr) * | 2016-04-20 | 2017-10-27 | Sealicone | Joint composite pour ouvrant ou partie mobile d'aeronef comprenant au moins un polymere hydrofuge- procede de fabrication dudit joint |
Also Published As
Publication number | Publication date |
---|---|
CA2915293A1 (fr) | 2014-12-18 |
FR3006993B1 (fr) | 2018-01-05 |
EP3007921A1 (fr) | 2016-04-20 |
BR112015031474A2 (pt) | 2017-07-25 |
FR3006993A1 (fr) | 2014-12-19 |
US20160114895A1 (en) | 2016-04-28 |
US10011363B2 (en) | 2018-07-03 |
CA2915293C (fr) | 2021-07-13 |
BR112015031474B1 (pt) | 2021-08-10 |
EP3007921B1 (fr) | 2019-02-20 |
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