BR112013022591A2 - janela em formato de losango para uma armação de avião compósita e/ou metálica - Google Patents
janela em formato de losango para uma armação de avião compósita e/ou metálicaInfo
- Publication number
- BR112013022591A2 BR112013022591A2 BR112013022591A BR112013022591A BR112013022591A2 BR 112013022591 A2 BR112013022591 A2 BR 112013022591A2 BR 112013022591 A BR112013022591 A BR 112013022591A BR 112013022591 A BR112013022591 A BR 112013022591A BR 112013022591 A2 BR112013022591 A2 BR 112013022591A2
- Authority
- BR
- Brazil
- Prior art keywords
- cutout
- composite
- shaped window
- diamond
- fuselage
- Prior art date
Links
- 239000002131 composite material Substances 0.000 title abstract 2
- 239000002184 metal Substances 0.000 title 1
- 229910003460 diamond Inorganic materials 0.000 abstract 1
- 239000010432 diamond Substances 0.000 abstract 1
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
- B64C1/14—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
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
-
- 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
- B64C1/068—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
- B64C1/14—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
- B64C1/1476—Canopies; Windscreens or similar transparent elements
- B64C1/1484—Windows
-
- 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
- B64C1/1476—Canopies; Windscreens or similar transparent elements
- B64C1/1492—Structure and mounting of the transparent elements in the window or windscreen
-
- 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
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T156/00—Adhesive bonding and miscellaneous chemical manufacture
- Y10T156/10—Methods of surface bonding and/or assembly therefor
- Y10T156/1052—Methods of surface bonding and/or assembly therefor with cutting, punching, tearing or severing
- Y10T156/1062—Prior to assembly
- Y10T156/1064—Partial cutting [e.g., grooving or incising]
-
- 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
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T83/00—Cutting
- Y10T83/04—Processes
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Moulding By Coating Moulds (AREA)
- Laminated Bodies (AREA)
Abstract
resumo patente de invenção: "janela em formato de losango para uma armação de avião compósita e/ou metálica". a presente invenção refere-se a uma fuselagem de aeronave que pode incluir uma seção cilíndrica (34) que tem uma região lateral. a fuselagem pode incluir um primeiro recorte (52a) e um segundo recorte (52b) formados na região lateral em uma relação lado a lado um com o outro. a fuselagem pode prover um percurso de carga direto se estendendo ao longo da seção cilíndrica. o percurso de carga pode se estender de forma substancialmente contínua a partir de uma porção inferior da região lateral geralmente sob o primeiro recorte até uma porção superior da região lateral geralmente sobre o segundo recorte.
Applications Claiming Priority (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US13/041,299 US8616500B2 (en) | 2011-03-04 | 2011-03-04 | Diamond shaped window for composite and/or metallic airframe |
US13/041,299 | 2011-03-04 | ||
PCT/US2012/023819 WO2012121825A1 (en) | 2011-03-04 | 2012-02-03 | Diamond shaped window for a composite and/or metallic airframe |
Publications (2)
Publication Number | Publication Date |
---|---|
BR112013022591A2 true BR112013022591A2 (pt) | 2016-12-06 |
BR112013022591B1 BR112013022591B1 (pt) | 2021-03-23 |
Family
ID=45582067
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
BR112013022591-2A BR112013022591B1 (pt) | 2011-03-04 | 2012-02-03 | Fuselagem de aeronave e método de formação de recortes em uma região lateral de uma fuselagem de aeronave |
Country Status (11)
Country | Link |
---|---|
US (2) | US8616500B2 (pt) |
EP (1) | EP2681112B1 (pt) |
JP (1) | JP6029599B2 (pt) |
KR (1) | KR101928114B1 (pt) |
CN (1) | CN103429493B (pt) |
AU (1) | AU2012226306B2 (pt) |
BR (1) | BR112013022591B1 (pt) |
CA (1) | CA2826143C (pt) |
ES (1) | ES2637594T3 (pt) |
RU (1) | RU2586768C2 (pt) |
WO (1) | WO2012121825A1 (pt) |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US9586699B1 (en) | 1999-08-16 | 2017-03-07 | Smart Drilling And Completion, Inc. | Methods and apparatus for monitoring and fixing holes in composite aircraft |
US9625361B1 (en) | 2001-08-19 | 2017-04-18 | Smart Drilling And Completion, Inc. | Methods and apparatus to prevent failures of fiber-reinforced composite materials under compressive stresses caused by fluids and gases invading microfractures in the materials |
US8939406B2 (en) * | 2012-07-02 | 2015-01-27 | The Boeing Company | Joining composite fuselage sections along window belts |
EP2746149B1 (en) * | 2012-12-19 | 2019-06-19 | Airbus Operations GmbH | Method for the production of a connecting element, connecting element, and aircraft or spacecraft |
FR3000470B1 (fr) * | 2012-12-28 | 2015-12-25 | Airbus Operations Sas | Peau auto-raidie pour fuselage d'aeronef comprenant des lisses a section fermee et procede de fabrication associe |
JP6310268B2 (ja) * | 2014-02-10 | 2018-04-11 | 株式会社とわに | 航空機用スクラップ処理装置 |
JP6309324B2 (ja) | 2014-03-28 | 2018-04-11 | 三菱重工業株式会社 | 複合材構造体、これを備えた航空機翼および航空機胴体、並びに複合材構造体の製造方法 |
FR3023826B1 (fr) * | 2014-07-18 | 2018-02-23 | Eads Sogerma | Structure linteau pour fuselage d'aeronef et fuselage comporant un tel linteau |
FR3027273B1 (fr) * | 2014-10-17 | 2018-04-27 | Arianegroup Sas | Architecture de paroi de face de voiture telle qu'une voiture de train en composite sandwich |
DE102015110165B4 (de) * | 2015-06-24 | 2017-03-02 | Airbus Operations Gmbh | Hautfeldfenstereinheit für ein Luftfahrzeug |
DE102016107740B4 (de) * | 2016-04-26 | 2018-02-15 | Benteler Automobiltechnik Gmbh | Achsträger mit verbessertem Lastpfad |
JP6768348B2 (ja) | 2016-05-26 | 2020-10-14 | 三菱重工業株式会社 | 胴体の断面形状設計方法、設計装置及び設計プログラム |
US10308342B2 (en) * | 2016-09-07 | 2019-06-04 | The Boeing Company | Method of repairing damage to fuselage barrel and associated apparatus and system |
US10293915B2 (en) | 2016-12-13 | 2019-05-21 | The Boeing Company | Apparatuses and methods for aerodynamic window assemblies |
CN108090265B (zh) * | 2017-12-08 | 2021-05-25 | 中国航空工业集团公司西安飞机设计研究所 | 一种飞机机身普通框在弯曲载荷下的应力计算方法 |
US11338899B2 (en) * | 2018-04-05 | 2022-05-24 | The Boeing Company | Joint for a metal airplane skin using metal matrix composite |
US10516232B2 (en) * | 2018-05-21 | 2019-12-24 | The Boeing Company | Electrical multi-connector feedthrough panel and method therefor |
CN108725743B (zh) * | 2018-06-14 | 2023-07-14 | 中国水利水电科学研究院 | 一种仰首式手抛小型固定翼无人机机身 |
CN113165280B (zh) | 2018-10-26 | 2023-02-21 | 阿里斯复合材料有限公司 | 纤维复合材料部件的设计和有效制造方法 |
JP7344029B2 (ja) * | 2019-07-19 | 2023-09-13 | 株式会社Subaru | 移動体の構造体、および移動体の構造体の製造方法 |
US11383817B2 (en) * | 2019-07-19 | 2022-07-12 | The Boeing Company | Modular fuselage assemblies for aircraft, aircraft including modular fuselage assemblies, and MEl'hods of assembling modular fuselage assemblies |
US20240025532A1 (en) * | 2022-07-21 | 2024-01-25 | The Boeing Company | Support structure for an aircraft |
Family Cites Families (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2473616A (en) * | 1946-01-19 | 1949-06-21 | Vickers Armstrongs Ltd | Elliptical boundary frame for openings in pressure cabins for aircraft |
DE1252533B (pt) * | 1965-11-10 | |||
US4278485A (en) * | 1978-08-02 | 1981-07-14 | The Boeing Company | Method of forming composite wound structure |
US4230293A (en) * | 1978-08-02 | 1980-10-28 | Boeing Commercial Airplane Company | Composite structure and method of making |
WO1983001237A1 (en) | 1981-09-30 | 1983-04-14 | Whitener, Philip, Charles | Composite structures window belt and method of making |
US4450661A (en) | 1981-09-30 | 1984-05-29 | The Boeing Company | Composite structures window belt and method of making |
DE4408476C2 (de) | 1994-03-14 | 1996-04-11 | Daimler Benz Aerospace Airbus | Rumpfhaut für ein Flugzeug |
RU2103200C1 (ru) * | 1996-10-29 | 1998-01-27 | Акционерное общество "Центр перспективных разработок" Акционерного общества "Центральный научно-исследовательский институт специального машиностроения" | Несущая труба-оболочка из композиционных материалов |
RU2103198C1 (ru) * | 1996-10-29 | 1998-01-27 | Акционерное общество "Центр перспективных разработок акционерного общества "Центральный научно-исследовательский институт специального машиностроения" | Несущая труба-оболочка, панель из композиционных материалов и узел соединения панелей |
US6318035B1 (en) | 1999-06-01 | 2001-11-20 | Lockheed Martin Corporation | Window frame assembly for use in an aircraft and associated method of manufacture |
US7014806B2 (en) * | 2002-03-08 | 2006-03-21 | Airbus Deutschland Gmbh | Method for producing a three-dimensional fiber reinforced ring frame component |
US6736352B2 (en) | 2002-06-25 | 2004-05-18 | The Boeing Company | Aircraft windows and associated methods for installation |
USD512365S1 (en) | 2002-06-25 | 2005-12-06 | The Boeing Company | Aircraft window |
DE102004025375B4 (de) * | 2004-05-24 | 2010-01-28 | Airbus Deutschland Gmbh | Fensterrahmen für Flugzeuge |
US7166251B2 (en) * | 2004-12-01 | 2007-01-23 | The Boeing Company | Segmented flexible barrel lay-up mandrel |
US8292226B2 (en) * | 2005-11-15 | 2012-10-23 | The Boeing Company | Weight-optimizing internally pressurized composite-body aircraft fuselages having near-elliptical cross sections |
US7766277B2 (en) * | 2006-01-19 | 2010-08-03 | The Boeing Company | Deformable forward pressure bulkhead for an aircraft |
DE102006044683A1 (de) * | 2006-02-07 | 2007-08-23 | Grob, Margret | Flugzeugkörper und Verfahren zu seiner Herstellung |
DE102006025930B4 (de) * | 2006-06-02 | 2008-09-11 | Airbus Deutschland Gmbh | Rumpfstruktur und Verfahren zur Herstellung einer Rumpfstruktur |
FR2911112B1 (fr) * | 2007-01-05 | 2009-02-13 | Airbus France Sas | Section de fuselage pour aeronef et aeronef comprenant une telle section |
US8449709B2 (en) * | 2007-05-25 | 2013-05-28 | The Boeing Company | Method of fabricating fiber reinforced composite structure having stepped surface |
DE102008007545A1 (de) * | 2008-02-05 | 2009-08-27 | Airbus Deutschland Gmbh | Lasttragendes und schadenstolerantes Laminatflugzeugfenster |
DE102008008386A1 (de) * | 2008-02-09 | 2009-08-13 | Airbus Deutschland Gmbh | Verfahren zur Herstellung eines FVW-Bauteils |
DE102008012282A1 (de) * | 2008-03-03 | 2009-09-17 | Airbus Deutschland Gmbh | Rumpfstruktur für Flugzeug |
RU2392122C1 (ru) * | 2008-11-05 | 2010-06-20 | Открытое акционерное общество Центральный научно-исследовательский институт специального машиностроения | Сетчатая оболочка вращения из композиционных материалов |
DE102009023856A1 (de) * | 2009-06-04 | 2010-12-09 | Airbus Operations Gmbh | Flugzeugrumpf |
DE102009057018B4 (de) * | 2009-12-04 | 2016-09-15 | Airbus Defence and Space GmbH | Flugzeugrumpfstruktur |
DE102009060876A1 (de) * | 2009-12-30 | 2011-07-14 | IMA Materialforschung und Anwendungstechnik GmbH, 01109 | Luft- oder Raumfahrzeughülle |
-
2011
- 2011-03-04 US US13/041,299 patent/US8616500B2/en active Active
-
2012
- 2012-02-03 JP JP2013556636A patent/JP6029599B2/ja active Active
- 2012-02-03 CA CA2826143A patent/CA2826143C/en active Active
- 2012-02-03 WO PCT/US2012/023819 patent/WO2012121825A1/en active Application Filing
- 2012-02-03 BR BR112013022591-2A patent/BR112013022591B1/pt active IP Right Grant
- 2012-02-03 ES ES12703672.1T patent/ES2637594T3/es active Active
- 2012-02-03 RU RU2013144411/11A patent/RU2586768C2/ru active
- 2012-02-03 AU AU2012226306A patent/AU2012226306B2/en active Active
- 2012-02-03 CN CN201280011516.5A patent/CN103429493B/zh active Active
- 2012-02-03 EP EP12703672.1A patent/EP2681112B1/en active Active
- 2012-02-03 KR KR1020137018805A patent/KR101928114B1/ko active IP Right Grant
-
2013
- 2013-11-21 US US14/086,288 patent/US9193483B2/en active Active
Also Published As
Publication number | Publication date |
---|---|
US8616500B2 (en) | 2013-12-31 |
CN103429493B (zh) | 2016-11-09 |
EP2681112B1 (en) | 2017-05-17 |
US20120223187A1 (en) | 2012-09-06 |
RU2586768C2 (ru) | 2016-06-10 |
CA2826143A1 (en) | 2012-09-13 |
EP2681112A1 (en) | 2014-01-08 |
RU2013144411A (ru) | 2015-04-10 |
JP6029599B2 (ja) | 2016-11-24 |
JP2014506854A (ja) | 2014-03-20 |
WO2012121825A1 (en) | 2012-09-13 |
AU2012226306B2 (en) | 2016-08-04 |
CA2826143C (en) | 2017-07-11 |
ES2637594T3 (es) | 2017-10-13 |
US9193483B2 (en) | 2015-11-24 |
CN103429493A (zh) | 2013-12-04 |
BR112013022591B1 (pt) | 2021-03-23 |
KR101928114B1 (ko) | 2018-12-11 |
KR20130140116A (ko) | 2013-12-23 |
US20140076477A1 (en) | 2014-03-20 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
BR112013022591A2 (pt) | janela em formato de losango para uma armação de avião compósita e/ou metálica | |
BR112015001506A2 (pt) | subarmação para veículo | |
BR112014000534A2 (pt) | painel externo lateral para veículo | |
BR112015007241A2 (pt) | arranjo de pista | |
BR112015028744A2 (pt) | artigo de calçado que tem parte do calcanhar com um componente de malha | |
BR112012025874B8 (pt) | Estrutura de assento com encosto flexível anatômico | |
BR112016007806A8 (pt) | recipiente metálico moldado, microestrutura e processo para a fabricação de um recipiente metálico moldado | |
BR112013024304A2 (pt) | pino de ancoragem e processo de produção | |
BR112014000175A2 (pt) | estrutura de corpo de veículo e método para montar estrutura de corpo de veículo | |
BR112013032315A2 (pt) | recipiente isolado | |
BR102012014769B8 (pt) | Estrutura de viga longitudinal de quadro para quadros de chassis de veículos utilitários, veículo utilitário e processo para a produção de uma viga longitudinal de quadro para uma estrutura de viga longitudinal de quadro | |
WO2010122200A3 (es) | Herrajes para la cogida del estabilizador vertical de cola de una aeronave. | |
BR112014009260A8 (pt) | sapata condutora deslizante para um elevador | |
BR112014012383A2 (pt) | superestrutura de carroceria de veículo | |
MY173932A (en) | Vehicle body rear structure | |
FR2984845B1 (fr) | Element de structure de fuselage d'aeronef anti deversement | |
BR112015023387A2 (pt) | composições lipídicas de racecodotril | |
MX363009B (es) | Barra de torsion posterior con seccion media abultada. | |
FR2951434B1 (fr) | Empennage horizontal d'aeronef muni d'un apex de bord d'attaque | |
FR2984844B1 (fr) | Element de structure de fuselage d'aeronef anti deversement | |
BR112014012968A2 (pt) | estrutura de instalação de peça de projeto para veículo | |
BR112014012469A2 (pt) | estrutura de seção lateral de carroceria de veículo | |
AR095458A1 (es) | Estructura a base de cartón | |
FR2978496B1 (fr) | Ensemble propulsif d'aeronef comprenant au moins un turboreacteur et une nacelle | |
WO2013128054A3 (es) | Estructura de refuerzo integrada en estructura interna de aeronave en material compuesto |
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] | ||
B09A | Decision: intention to grant [chapter 9.1 patent gazette] | ||
B16A | Patent or certificate of addition of invention granted [chapter 16.1 patent gazette] |
Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 03/02/2012, OBSERVADAS AS CONDICOES LEGAIS. |