BR112015015227A2 - dispositivo de absorção de energia para elemento de estrutura de aeronave - Google Patents

dispositivo de absorção de energia para elemento de estrutura de aeronave

Info

Publication number
BR112015015227A2
BR112015015227A2 BR112015015227A BR112015015227A BR112015015227A2 BR 112015015227 A2 BR112015015227 A2 BR 112015015227A2 BR 112015015227 A BR112015015227 A BR 112015015227A BR 112015015227 A BR112015015227 A BR 112015015227A BR 112015015227 A2 BR112015015227 A2 BR 112015015227A2
Authority
BR
Brazil
Prior art keywords
foam core
impact
outer shell
kinetic energy
absorbing device
Prior art date
Application number
BR112015015227A
Other languages
English (en)
Inventor
Petiot Caroline
Mesnage Didier
Bermudez Michel
Original Assignee
European Aeronautic Defence & Space Co Eads France
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 European Aeronautic Defence & Space Co Eads France filed Critical European Aeronautic Defence & Space Co Eads France
Publication of BR112015015227A2 publication Critical patent/BR112015015227A2/pt

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C7/00—Structures or fairings not otherwise provided for
    • 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
    • B64C1/061—Frames
    • B64C1/062—Frames specially adapted to absorb crash loads
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/205—Constructional features for protecting blades, e.g. coating
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • B64C11/26—Fabricated blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/20—Integral or sandwich constructions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • 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
    • B32B5/00—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts
    • B32B5/22—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed
    • B32B5/24—Layered products characterised by the non- homogeneity or physical structure, i.e. comprising a fibrous, filamentary, particulate or foam layer; Layered products characterised by having a layer differing constitutionally or physically in different parts characterised by the presence of two or more layers which are next to each other and are fibrous, filamentary, formed of particles or foamed one layer being a fibrous or filamentary layer
    • 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
    • B32B7/08—Interconnection of layers by mechanical means
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/16—Blades
    • B64C11/20—Constructional features
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • 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
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • 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
    • 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
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Vibration Dampers (AREA)
  • Laminated Bodies (AREA)

Abstract

resumo patente de invenção: "dispositivo de absorção de energia para elemento de estrutura de aeronave". a invenção se refere a um dispositivo de absorção de energia cinética para elemento de estrutura de aeronave, capaz de ser submetido a um impacto dinâmico, esse dispositivo comportando: - um envoltório externo (21) em material compósito trançado apto a conservar, após impacto, uma integridade; - um núcleo em espuma (22) contido no envoltório externo e apto a encher pelo menos parcialmente esse envoltório externo (21), esse núcleo em espuma (22) estando apto a absorver pelo menos parcialmente a energia cinética gerada pelo impacto; e - elementos de reforço (30) integrados pelo menos em parte no núcleo em espuma para dissipar, em associação com o núcleo em espuma (22), a energia cinética gerada pelo impacto; - os elementos de reforço (30) compreendendo fios descontínuos (32) inseridos por picotagem no núcleo em espuma (22); e - os fios descontínuos (32) comportam, cada um, uma cabeça (33) em l ou em t, rebatida no exterior do envoltório externo (21).
BR112015015227A 2012-12-27 2013-12-16 dispositivo de absorção de energia para elemento de estrutura de aeronave BR112015015227A2 (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1262895A FR3000463B1 (fr) 2012-12-27 2012-12-27 Dispositif d'absorption d'energie pour element de structure d'aeronef
PCT/EP2013/076731 WO2014102082A1 (fr) 2012-12-27 2013-12-16 Dispositif d'absorption d'énergie pour élément de structure d'aéronef

Publications (1)

Publication Number Publication Date
BR112015015227A2 true BR112015015227A2 (pt) 2017-07-11

Family

ID=48044832

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112015015227A BR112015015227A2 (pt) 2012-12-27 2013-12-16 dispositivo de absorção de energia para elemento de estrutura de aeronave

Country Status (9)

Country Link
US (1) US9611030B2 (pt)
EP (1) EP2938536B1 (pt)
CN (1) CN105008220B (pt)
BR (1) BR112015015227A2 (pt)
CA (1) CA2895547C (pt)
ES (1) ES2656665T3 (pt)
FR (1) FR3000463B1 (pt)
RU (1) RU2644811C2 (pt)
WO (1) WO2014102082A1 (pt)

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USD293199S (en) * 1984-07-16 1987-12-15 Grenley J David Hand-held can opener
FR3000464B1 (fr) * 2012-12-27 2016-01-15 Eads Europ Aeronautic Defence Dispositif d'absorption d'energie pour element de structure d'aeronef
ES2799935T3 (es) 2016-02-29 2020-12-22 Airbus Operations Sl Perfil aerodinámico de aeronave con un borde de salida unido por puntos y procedimiento de fabricación del mismo
CA2948710C (en) 2016-03-11 2024-01-16 Dometic Sweden Ab Power wand and method of use
CN206170762U (zh) * 2016-06-13 2017-05-17 亿航智能设备（广州）有限公司 螺旋桨和机身
CN106273559A (zh) * 2016-08-10 2017-01-04 北京汽车集团有限公司 一种汽车结构件的成型方法及汽车结构件
USD846505S1 (en) * 2016-11-17 2019-04-23 Dometic Sweden Ab Power wand
EP3335986B1 (en) * 2016-12-19 2019-11-20 Airbus Operations S.L. Impact resistant dorsal fin
USD893455S1 (en) * 2017-12-29 2020-08-18 Harman International Industries, Incorporated Soundbar
US11459085B2 (en) * 2019-04-30 2022-10-04 Textron Innovations Inc. Energy attenuation stabilizers and methods
US11518502B2 (en) * 2019-04-30 2022-12-06 Textron Innovations Inc. Energy absorption stabilizers and methods
US11795827B1 (en) * 2022-04-04 2023-10-24 General Electric Company Airfoil assembly with a structurally reinforced foam core

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4302155A (en) * 1979-01-08 1981-11-24 Hartzell Propeller, Inc. Air craft propeller assembly with composite blades
GB2066731B (en) * 1979-11-28 1983-12-07 Nat Res Dev Conformable reinforcement board
FR2748719B1 (fr) * 1987-06-26 1999-05-07 Aerospatiale Pale a faible signature radar
FR2684719B1 (fr) * 1991-12-04 1994-02-11 Snecma Aube de turbomachine comprenant des nappes de materiau composite.
DE69434917T2 (de) * 1993-05-04 2007-11-08 Foster-Miller, Inc., Waltham Gittergestützte verbundplatte mit schaumkern
EP1265744B1 (en) * 1999-12-28 2016-03-09 Milliken & Company Fiber reinforced composite cores
EP1475304B1 (en) * 2003-05-09 2009-09-02 Pilatus Flugzeugwerke Ag Aircraft wing
DE102005024408A1 (de) * 2005-05-27 2006-11-30 Airbus Deutschland Gmbh Verstärkung von Schaumwerkstoffen
FR2904604B1 (fr) * 2006-08-04 2009-02-27 Airbus France Sas Element de structure d'un aeronef
DE102008042452A1 (de) * 2008-09-29 2010-04-08 Airbus Deutschland Gmbh Faserverbundbauteil zur Energieabsorption im Crash-Fall für ein Luft- oder Raumfahrzeug, Rumpfstrukturabschnitt eines Luft- oder Raumfahrzeugs und Luft- oder Raumfahrzeug
DE102010027696A1 (de) * 2010-07-20 2012-01-26 Airbus Operations Gmbh Hauptlast-tragende Beplankungsschale sowie Strukturbauteil mit zumindest einer hauptlast-tragenden Beplankungsschale

Also Published As

Publication number Publication date
FR3000463A1 (fr) 2014-07-04
US20150344125A1 (en) 2015-12-03
CA2895547C (fr) 2020-03-24
WO2014102082A1 (fr) 2014-07-03
CN105008220A (zh) 2015-10-28
CA2895547A1 (fr) 2014-07-03
CN105008220B (zh) 2017-07-28
FR3000463B1 (fr) 2016-02-05
EP2938536A1 (fr) 2015-11-04
RU2644811C2 (ru) 2018-02-14
RU2015130607A (ru) 2017-01-27
ES2656665T3 (es) 2018-02-28
EP2938536B1 (fr) 2017-12-13
US9611030B2 (en) 2017-04-04

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Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B11B Dismissal acc. art. 36, par 1 of ipl - no reply within 90 days to fullfil the necessary requirements