ES2384250A1 - Unión de elementos estructurales de aeronave. - Google Patents

Unión de elementos estructurales de aeronave. Download PDF

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Publication number
ES2384250A1
ES2384250A1 ES200930772A ES200930772A ES2384250A1 ES 2384250 A1 ES2384250 A1 ES 2384250A1 ES 200930772 A ES200930772 A ES 200930772A ES 200930772 A ES200930772 A ES 200930772A ES 2384250 A1 ES2384250 A1 ES 2384250A1
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ES
Spain
Prior art keywords
technical
document
section
union
state
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Legal status (The legal status 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 status listed.)
Granted
Application number
ES200930772A
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English (en)
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ES2384250B1 (es
Inventor
José María Pina López
Enrique VERA VILLARES
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Airbus Operations SL
Original Assignee
Airbus Operations SL
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 Airbus Operations SL filed Critical Airbus Operations SL
Priority to ES200930772A priority Critical patent/ES2384250B1/es
Priority to US12/629,805 priority patent/US20110073711A1/en
Priority to PCT/ES2010/070637 priority patent/WO2011039402A2/es
Publication of ES2384250A1 publication Critical patent/ES2384250A1/es
Application granted granted Critical
Publication of ES2384250B1 publication Critical patent/ES2384250B1/es
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/064—Stringers; Longerons
    • 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
    • B64C1/065—Spars
    • 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
    • B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
    • B29C65/56—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using mechanical means or mechanical connections, e.g. form-fits
    • B29C65/60—Riveting or staking
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/50—General aspects of joining tubular articles; General aspects of joining long products, i.e. bars or profiled elements; General aspects of joining single elements to tubular articles, hollow articles or bars; General aspects of joining several hollow-preforms to form hollow or tubular articles
    • B29C66/51—Joining tubular articles, profiled elements or bars; Joining single elements to tubular articles, hollow articles or bars; Joining several hollow-preforms to form hollow or tubular articles
    • B29C66/52—Joining tubular articles, bars or profiled elements
    • B29C66/524—Joining profiled elements
    • B29C66/5241—Joining profiled elements for forming coaxial connections, i.e. the profiled elements to be joined forming a zero angle relative to each other
    • 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
    • B29C66/00—General aspects of processes or apparatus for joining preformed parts
    • B29C66/70—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material
    • B29C66/72—General aspects of processes or apparatus for joining preformed parts characterised by the composition, physical properties or the structure of the material of the parts to be joined; Joining with non-plastics material characterised by the structure of the material of the parts to be joined
    • B29C66/721—Fibre-reinforced materials
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
    • B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
    • B29L2031/00—Other particular articles
    • B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
    • B29L2031/3076—Aircrafts
    • 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
    • F16B—DEVICES FOR FASTENING OR SECURING CONSTRUCTIONAL ELEMENTS OR MACHINE PARTS TOGETHER, e.g. NAILS, BOLTS, CIRCLIPS, CLAMPS, CLIPS OR WEDGES; JOINTS OR JOINTING
    • F16B5/00—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them
    • F16B5/04—Joining sheets or plates, e.g. panels, to one another or to strips or bars parallel to them by means of riveting

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Connection Of Plates (AREA)
  • Information Retrieval, Db Structures And Fs Structures Therefor (AREA)

Abstract

Unión de elemento estructural (1) de aeronave que tiene una sección en forma de omega con otro elemento estructural de aeronave (10) que tiene una sección diferente, comprendiendo la citada unión de estos elementos estructurales (1, 10) con diferente sección al menos dos elementos de unión (4) en forma de angular que se unen con la faldilla exterior (5) de los elementos estructurales (1, 10), de tal modo que esta unión consigue que el paso de sección se realice de forma continua, mediante elementos (4) sencillos en su fabricación y montaje, gracias a su simplicidad geométrica, siendo además el montaje de esta unión de elementos estructurales (1, 10) con un cambio de sección de una gran flexibilidad, permitiendo absorber las tolerancias de la unión, y consiguiendo que el reparto de cargas entre los elementos estructurales (1, 10) y los elementos de unión (4) sea óptimo.

Claims (1)

  1. REIVINDICACIONES
    OFRCRNA�ES�AAOL�
    DE��ATENTES�R�MARCA�
    21 N2O�soaicitud:2 2
    ES�AA�
    22 Fecha�de�presentaci6n�de�aa�soaicitud:� 22
    2 Fecha�de�prioridad:
    RNFORME�SOBRE�EL�ESTADO�DE�LA�TCCNRCA
    51 nt C B64C1106 �22��62�1)�
    DOCUMENTOS�RELEAANTES�
    Categoria
    @ Documentos citados Reivindicaciones afectadas
    x x E WO�2� 4 �8�A1�2ARRBUS� �ERATRONS)�112��22 8 pagina�68�ainea�16�p�pagina 8�ainea�6��pagina�88�ainea�15�p�pagina �8�ainea�28��diguras�1 2 WO2 51 ���A2�2ARRBUS�DEUTSCHLAND)��6� 822 � reivindicaciones�184 �81���diguras �4� DE�12 8�18 ��2�A1�2ARRBUS�DEUTSCHLAND)�2221�22 � parrados�6��1�[86��22[86��26[8� ��55[86��5�[86��61[��diguras�6 82 1�1� 1�688�11 1�688�11
    Categoria�de�aos�documentos�citados x:�de�particuaar�reaevanci� R:�de�particuaar�reaevancia�comiinado�con�otro/s�de�a� �����misma�categori� A:�redaeaa�ea�estado�de�aa�tdcnica� O:�rederido�a�divuagaci6n�no�escrita �:�puiaicado�entre�aa�decha�de�prioridad�yaa�de�presentaci6n ����de�aa�soaicitu� E:�documento�anterior8�pero�puiaicado�despuds�de�aa�dech� �����de�presentaci6n�de�aa�soaicitud
    E presente informe ha sido rea izado � para�todas�aas�reivindicaciones � para�aas�reivindicaciones�nO:�
    Fecha de rea izaci6n de informe 2�2�622 12 Examinador L2�.2�Duenas�Campo Pagina 1/4
    RNFORME�SOBRE�EL�ESTADO�DE LA�TCCNRCA
    NO�de�soaicitud: 2
    Documentaci6n�minima�iuscada�2sistema�de�caasidicaci6n�seguido de�aos simioaos de�caasidicaci6n) B64C Bases de datos eaectr6nicas consuatadas durante aa iusqueda 2nomire de aa iase de datos y8 si es posiiae8 tdrminos de
    iusqueda�utiaizados) RNAENES8�E�ODOC
    Rndorme�soire ea�estado�de�aa�tdcnica agina�2/4
    OP N ON EsCR TA
    NO�de�soaicitud:�22
    Fecha�de�reaaizaci6n�de�aa�opini6n�escrita:2 �2�622 12
    Dec araci6n
    Novedad (Art
    1 LP 11/198 ) Reivindicaciones si
    Reivindicaciones 1 �11
    NO
    Actividad inventiva (Art 8 1 LP11/198 )
    Reivindicaciones si
    Reivindicaciones 1 �11
    NO
    Se�considera�que�aa�soaicitud cumpae�con�ea requisito�de�apaicaci6n�industriaa2�Este�requisito�due�evaauado�durante�aa�dase�de examen�dormaa y tdcnico�de�aa soaicitud�2Articuao 122�Ley�11/1�86)2
    Base de a opini6n
    La�presente�opini6n�se ha�reaaizado�soire�aa iase�de�aa�soaicitud�de�patente�taa y �como�se �puiaica2
    Rndorme�soire ea�estado�de�aa�tdcnica agina��/4
    OP N ON EsCR TA
    NO�de�soaicitud:�22
    1 Documentos considerados
    A�continuaci6nse reaacionan�aos�documentos pertenecientes aa�estado de aa�tdcnica�tomados en�consideraci6n para�aa reaaizaci6n�de�esta�opini6n2
    Documento
    Numero de pub icaci6n o identificaci6n Fecha de pub icaci6n
    D1
    WO�21 4 �8�A1�2ARRBUSO �ERATRONS) 112��22
    D2
    WO2 51 ���A2�2ARRBUS�DEUTSCHLAND) �62�822
    D
    DE�12 8�18 ��2�A1�2ARRBUS�DEUTSCHLAND) 2221�22
    2 Dec araci6n motivada segun os articu os 29 y 29 7 de Reg amento de ejecuci6n de a Ley 11/198 , de 20 de marzo, de Patentes sobre a novedad y a actividad inventiva; citas y exp icaciones en apoyo de esta dec araci6n
    La�soaicitud�de invenci6n�presentada�contiene�una�reivindicaci6n�principaa o�independiente�de�aparato y diez reivindicaciones mas dependientes de�aa�anterior2�Dicha invenci6n�dedine �como�oiaeto�tdcnico�de �aa misma8�segun�se expresa�en�aas primeras aineas de aa reivindicaci6n principaa8 una uni6n de un eaemento estructuraa con otro eaemento estructuraa� dicho oiaeto tdcnico se centra duncionaamente o como apaicaci6n8 segun se continua en ea preamiuao de dicha reivindicaci6n principaa8 en ea campo�de�aas aeronaves2Rguaamente8 y�como�estaiaece�ea �soaicitante�en�ea �preamiuao�de�dicha�reivindicaci6n�principaa8 aa invenci6n�incauye �como �parte dea estado�de�aa�tdcnica de dicho�campo�tecnoa6gico�ea�que �ea primer eaemento estructuraa �tiene una�secci6n�en�omega�y�ea otro�eaemento�tiene�una�secci6n�diderente2�La�parte�esenciaa�de�aa�invenci6n�que�destaca�ea soaicitante como novedosa drente aa estado de aa tdcnica de cara a resoaver ea proiaema tdcnico paanteado y8 por tanto8 aas caracteristicas tdcnicas suistanciaaes dea aparato que de manera necesaria o sudiciente adrontan dicho proiaema tdcnico8 estaiaecidas segun�ea �soaicitante�en�aa�parte�caracterizadora�de�aa�reivindicaci6n�independiente8�comprende�ea�que�aa�citada uni6n�se reaaiza�mediante�dos eaementos de�uni6n�en�dorma�de�anguaar que�se unen�con�aa�daadiaaa�exterior�de�aos eaementos estructuraaes2 Tamiidn�incauye�aa�simpaicidad8�senciaaez8 �continuidad y�daexiiiaidad�de�aa�soauci6n8�aunque�esto�es ea�proiaema a�resoaver�o�ea oiaetivo�a�conseguir8�por �ao�que�no�anade�caracteristicas tdcnicas a�aa�reivindicaci6n�principaa2
    Ea�documento�D�1�se�considera�ea�estado�de�aa�tdcnica�mas�pr6ximo2�Este�documento CT8�que�dorma�parte�deamismo sector�tdcnico8�presenta�una�interconexi6n�estructuraa�entre�un�aargueriaao�de�secci6n�en T�y�otro�de�secci6n�en�omega2�La uni6n�se�reaaiza�mediante�dos�anguaares�apoyados�en�aos�pies�de�amios�aargueriaaos2Ea�documentoD 1�es8por�tanto8 reaevante�en�ao �que�concierne �a�esta�reivindicaci6n�12
    Ea documento D2 esta tamiidn iastante reaacionado con aa soaicitud de invenci6n presentada y tamiidn dorma parte dea mismo sector tecnoa6gico2 Se trata de un documento CT y muestra una conexi6n estructuraa entre un aargueriaao de secci6n en T y otro de secci6n en omega2 La uni6n se reaaiza8 entre otros eaementos8 mediante dos anguaares apoyados en aos pies de�amios aargueriaaos2 Ea �documentoD �2�es8�por �tanto8�reaevante�en�ao�que�concierne a�esta�reivindicaci6n�12
    �or�otra�parte8�aas reivindicaciones dependientes 2�11 podrian�encontrarse�descritas en�aaguno de aos dos documentos citados8 aa menos en sus caracteristicas tdcnicas esenciaaes2 Rguaamente8 y no tomando en consideraci6n aqueaaas caracteristicas�tdcnicas estimadas como ampaiamente�conocidas�en�ea�estado de aa�tdcnicao �que�pueden�ser�meras yuxtaposiciones de�otras caracteristicas de�diseno�propias dea�desarroaao�o�traiaao�tdcnico�normaa y no�inventivo de un experto�en�aa materia8�aas reivindicaciones dependientes 2 11�pueden presentar�un�reducido�contenido�de�saato�inventivo�que duera�susceptiiae�de�ampaiar�o�compaementar�ea�correspondiente�de�aareivindicaci6nprincipaa2�Las�reivindicaciones�1 ��11 incauyen�ea�procedimiento�de�dairicaci6n�de�dichos eaementos de�uni6n8�aunque�esto�no�puede�dedinir mas aa�invenci6n�por tratarse�de�una �reivindicaci6n de�aparato8 �por �ao�que�no�anaden�caracteristicas tdcnicas2
    Ea documento D esta tamiidn iastante reaacionado con aa soaicitud de invenci6n presentada y tamiidn dorma parte dea mismo�sector�tecnoa6gico2�Se trata�de�un�documento aaeman y muestra�tamiidn�una uni6n estructuraa entre�un�aargueriaao de secci6n en T y otro de secci6n en omega2 La uni6n se reaaiza8 entre otros eaementos8 mediante dos anguaares apoyados en aos pies de�amios aargueriaaos2
    Rndorme soire ea estado�de�aa�tdcnica agina�4/4
ES200930772A 2009-09-30 2009-09-30 Unión de elementos estructurales de aeronave. Active ES2384250B1 (es)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES200930772A ES2384250B1 (es) 2009-09-30 2009-09-30 Unión de elementos estructurales de aeronave.
US12/629,805 US20110073711A1 (en) 2009-09-30 2009-12-02 Joining of structural aircraft elements
PCT/ES2010/070637 WO2011039402A2 (es) 2009-09-30 2010-09-30 Unión de elementos estructurales de aeronave

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ES200930772A ES2384250B1 (es) 2009-09-30 2009-09-30 Unión de elementos estructurales de aeronave.

Publications (2)

Publication Number Publication Date
ES2384250A1 true ES2384250A1 (es) 2012-07-03
ES2384250B1 ES2384250B1 (es) 2013-05-16

Family

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Family Applications (1)

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ES200930772A Active ES2384250B1 (es) 2009-09-30 2009-09-30 Unión de elementos estructurales de aeronave.

Country Status (3)

Country Link
US (1) US20110073711A1 (es)
ES (1) ES2384250B1 (es)
WO (1) WO2011039402A2 (es)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2781450B1 (en) 2013-03-19 2018-05-02 Airbus Operations GmbH System and method for interconnecting composite structures
US10745104B2 (en) * 2018-03-02 2020-08-18 The Boeing Company Stringer transition through a common base charge

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009095133A2 (de) * 2008-01-30 2009-08-06 Airbus Operations Gmbh Verbindungsanordnung zum verbinden zweier versteifungselemente unterschiedlichen querschnittprofils für ein luft- oder raumfahrzeug, und ein schalenbauteil
WO2009109438A1 (de) * 2008-03-03 2009-09-11 Airbus Operations Gmbh Verbund sowie luft- oder raumfahrzeug mit einem derartigen verbund
DE102008018772A1 (de) * 2008-04-14 2009-10-22 Airbus Deutschland Gmbh Verbindungsanordnung zum Verbinden eines ersten und zweiten Versteifungselementes für ein Luft- oder Raumfahrzeug, und ein Schalenbauteil

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2406315A (en) * 1943-01-06 1946-08-27 Cons Vultee Aircraft Corp Clip
FR2910874B1 (fr) * 2007-01-02 2009-02-13 Airbus France Sas Lisses assemblees au niveau d'une jonction circonferentielle d'un fuselage d'avion.
FR2922516B1 (fr) * 2007-10-18 2010-04-16 Airbus France Eclissage de raidisseurs en omega au niveau d'une jonction circonferentielle d'un fuselage d'avion
DE102008010197B4 (de) * 2008-02-20 2012-03-22 Airbus Operations Gmbh Verfahren zum Verbinden von zwei Rumpfsektionen unter Schaffung eines Querstoßes sowie Querstoßverbindung
US8220745B2 (en) * 2008-04-14 2012-07-17 Airbus Deutschland Gmbh Connection arrangement for connecting a first and second reinforcing element for an aircraft or spacecraft, and a shell component
DE102008002117B4 (de) * 2008-05-30 2013-10-31 Airbus Operations Gmbh Verbund und Struktur

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009095133A2 (de) * 2008-01-30 2009-08-06 Airbus Operations Gmbh Verbindungsanordnung zum verbinden zweier versteifungselemente unterschiedlichen querschnittprofils für ein luft- oder raumfahrzeug, und ein schalenbauteil
WO2009109438A1 (de) * 2008-03-03 2009-09-11 Airbus Operations Gmbh Verbund sowie luft- oder raumfahrzeug mit einem derartigen verbund
DE102008018772A1 (de) * 2008-04-14 2009-10-22 Airbus Deutschland Gmbh Verbindungsanordnung zum Verbinden eines ersten und zweiten Versteifungselementes für ein Luft- oder Raumfahrzeug, und ein Schalenbauteil

Also Published As

Publication number Publication date
US20110073711A1 (en) 2011-03-31
WO2011039402A3 (es) 2011-10-06
ES2384250B1 (es) 2013-05-16
WO2011039402A2 (es) 2011-04-07

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