BR0315127A - Dispositivo de painel de aeronave, conjunto estrutural de aeronave, e método de prevenção de danos causados por uma corrente elétrica gerada por um impacto de raio sobre um conjunto estrutural de aeronave incluindo uma subestrutura e um dispositivo de painel de aeronave - Google Patents

Dispositivo de painel de aeronave, conjunto estrutural de aeronave, e método de prevenção de danos causados por uma corrente elétrica gerada por um impacto de raio sobre um conjunto estrutural de aeronave incluindo uma subestrutura e um dispositivo de painel de aeronave

Info

Publication number
BR0315127A
BR0315127A BR0315127-1A BR0315127A BR0315127A BR 0315127 A BR0315127 A BR 0315127A BR 0315127 A BR0315127 A BR 0315127A BR 0315127 A BR0315127 A BR 0315127A
Authority
BR
Brazil
Prior art keywords
aircraft
structural assembly
substructure
preventing damage
aircraft structural
Prior art date
Application number
BR0315127-1A
Other languages
English (en)
Inventor
Doan D Pham
Mark W Tollan
Gregory R Gleason
Original Assignee
Boeing Co
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 Boeing Co filed Critical Boeing Co
Publication of BR0315127A publication Critical patent/BR0315127A/pt

Links

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
    • B64D45/00—Aircraft indicators or protectors not otherwise provided for
    • B64D45/02—Lightning protectors; Static dischargers
    • 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
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)
  • Elimination Of Static Electricity (AREA)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)
  • Buildings Adapted To Withstand Abnormal External Influences (AREA)
  • Details Of Aerials (AREA)
  • Electrically Operated Instructional Devices (AREA)
  • Medicines Containing Plant Substances (AREA)

Abstract

"DISPOSITIVO DE PAINEL DE AERONAVE, CONJUNTO ESTRUTURAL DE AERONAVE, E MéTODO DE PREVENçãO DE DANOS CAUSADOS POR UMA CORRENTE ELéTRICA GERADA POR UM IMPACTO DE RAIO SOBRE UM CONJUNTO ESTRUTURAL DE AERONAVE INCLUINDO UMA SUBESTRUTURA E UM DISPOSITIVO DE PAINEL DE AERONAVE". Trata-se de um dispositivo de painel de aeronave (10), incluindo um núcleo de painel (28), uma pluralidade de camadas de material pré-impregnado (30) envolvendo o núcleo de painel (28) formando uma camada interna de folhas, pelo menos uma camada de filme metálico (38) posicionada sobre uma camada externa da camada interna de folhas. A pelo menos uma camada de filme metálico (38) proporciona um condutor elétrico entre a superfície externa (24) do dispositivo de painel de aeronave (10) e a subestrutura (26) para propósitos de aterramento.
BR0315127-1A 2002-10-11 2003-10-07 Dispositivo de painel de aeronave, conjunto estrutural de aeronave, e método de prevenção de danos causados por uma corrente elétrica gerada por um impacto de raio sobre um conjunto estrutural de aeronave incluindo uma subestrutura e um dispositivo de painel de aeronave BR0315127A (pt)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US10/269,194 US7014143B2 (en) 2002-10-11 2002-10-11 Aircraft lightning strike protection and grounding technique
PCT/US2003/031807 WO2004033293A1 (en) 2002-10-11 2003-10-07 Lightning strike protection and grounding of a composite aircraft panel

Publications (1)

Publication Number Publication Date
BR0315127A true BR0315127A (pt) 2005-08-16

Family

ID=32068719

Family Applications (1)

Application Number Title Priority Date Filing Date
BR0315127-1A BR0315127A (pt) 2002-10-11 2003-10-07 Dispositivo de painel de aeronave, conjunto estrutural de aeronave, e método de prevenção de danos causados por uma corrente elétrica gerada por um impacto de raio sobre um conjunto estrutural de aeronave incluindo uma subestrutura e um dispositivo de painel de aeronave

Country Status (11)

Country Link
US (1) US7014143B2 (pt)
EP (1) EP1549545B1 (pt)
JP (1) JP4601428B2 (pt)
AT (1) ATE403597T1 (pt)
AU (1) AU2003282756A1 (pt)
BR (1) BR0315127A (pt)
CA (1) CA2501503C (pt)
DE (1) DE60322725D1 (pt)
ES (1) ES2310249T3 (pt)
IL (1) IL167853A (pt)
WO (1) WO2004033293A1 (pt)

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US7277266B1 (en) 2006-03-29 2007-10-02 The Boeing Company Lightning protection system for composite structure
DE102006035847B4 (de) * 2006-08-01 2009-11-19 Airbus Deutschland Gmbh Strukturanordnung sowie Verfahren zum Herstellen eines Bauteils für die Luft-und Raumfahrt
GB0619539D0 (en) 2006-10-04 2006-11-15 Hexcel Composites Ltd Curable resin films
US20100096063A1 (en) * 2006-11-13 2010-04-22 Friddell S Douglas Inspectability of composite items
US7678997B2 (en) * 2006-12-19 2010-03-16 The Boeing Company Large area circuitry using appliqués
US20080277531A1 (en) * 2007-05-11 2008-11-13 The Boeing Company Hybrid Composite Panel Systems and Methods
US7968169B2 (en) * 2007-08-07 2011-06-28 The Boeing Company Compound contoured composite beams and fabrication methods
US8206823B2 (en) * 2008-04-14 2012-06-26 The Boeing Company System and method for fabrication of integrated lightning strike protection material
US8645113B2 (en) * 2008-07-09 2014-02-04 The Boeing Company Methods and systems for evaluating a design of an aircraft
US20100108342A1 (en) * 2008-10-31 2010-05-06 Dexmet Corporation Layered structure with outer lightning protection surface
CN102458996B (zh) 2009-04-17 2016-11-16 3M创新有限公司 具有图案化导体的防雷板
BRPI1006590B1 (pt) 2009-04-17 2020-04-14 3M Innovative Properties Co revestimento de proteção contra raios
WO2010144770A1 (en) * 2009-06-12 2010-12-16 Lord Corporation Method for shielding a substrate from electromagnetic interference
US9681527B2 (en) * 2013-03-29 2017-06-13 The Boeing Company Method and apparatus for providing a current return network in an aircraft structure
US20160114883A1 (en) * 2014-10-23 2016-04-28 The Boeing Company Actively-controlled superhydrophobic surfaces
US10053203B2 (en) * 2015-10-13 2018-08-21 The Boeing Company Composite stiffener with integral conductive element
US10155373B2 (en) * 2015-10-16 2018-12-18 Quest Integrated, Llc Printed multifunctional skin for aerodynamic structures, and associated systems and methods
WO2019202472A2 (en) 2018-04-17 2019-10-24 3M Innovative Properties Company Conductive films
JP7034849B2 (ja) * 2018-06-28 2022-03-14 三菱重工業株式会社 複合材、複合材の製造方法、及び複合材の硬化方法
JP7039401B2 (ja) * 2018-06-28 2022-03-22 三菱重工業株式会社 複合材及び複合材の硬化方法
US11477888B2 (en) * 2018-10-08 2022-10-18 Quest Integrated, Llc Printed multifunctional skin for aerodynamic structures and associated systems and methods

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Also Published As

Publication number Publication date
AU2003282756A1 (en) 2004-05-04
IL167853A (en) 2009-06-15
CA2501503A1 (en) 2004-04-22
DE60322725D1 (de) 2008-09-18
ES2310249T3 (es) 2009-01-01
ATE403597T1 (de) 2008-08-15
EP1549545B1 (en) 2008-08-06
EP1549545A1 (en) 2005-07-06
US7014143B2 (en) 2006-03-21
US20040069895A1 (en) 2004-04-15
CA2501503C (en) 2009-05-26
JP4601428B2 (ja) 2010-12-22
JP2006502046A (ja) 2006-01-19
WO2004033293A1 (en) 2004-04-22

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Legal Events

Date Code Title Description
B11A Dismissal acc. art.33 of ipl - examination not requested within 36 months of filing
B11Y Definitive dismissal - extension of time limit for request of examination expired [chapter 11.1.1 patent gazette]