ES2405155R1 - Zonas de terminacion de larguerillos optimizadas en componentes de aeronaves - Google Patents

Zonas de terminacion de larguerillos optimizadas en componentes de aeronaves

Info

Publication number
ES2405155R1
ES2405155R1 ES201131711A ES201131711A ES2405155R1 ES 2405155 R1 ES2405155 R1 ES 2405155R1 ES 201131711 A ES201131711 A ES 201131711A ES 201131711 A ES201131711 A ES 201131711A ES 2405155 R1 ES2405155 R1 ES 2405155R1
Authority
ES
Spain
Prior art keywords
stringer
optimized
termination
aircraft components
foot
Prior art date
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
ES201131711A
Other languages
English (en)
Other versions
ES2405155B1 (es
ES2405155A2 (es
Inventor
Ruiz Francisco Javier Honorato
Lopez Jose Maria Pina
Vines Pedro Nogueroles
Pastor Augusto Perez
De La Llave Cesar Bautista
Garrofe Pablo Cebolla
Hidalgo Alberto Arana
Garcia Aquilino Garcia
Blanco Jorge Juan Galiana
Glowacz Ewa Aneta
Alonso Alejandro Fernandez
Sacristan Angel Garcia
Fuentes Carolina Elena Frias
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 ES201131711A priority Critical patent/ES2405155B1/es
Priority to US13/608,509 priority patent/US20130101801A1/en
Priority to PCT/ES2012/070733 priority patent/WO2013060916A1/es
Publication of ES2405155A2 publication Critical patent/ES2405155A2/es
Publication of ES2405155R1 publication Critical patent/ES2405155R1/es
Application granted granted Critical
Publication of ES2405155B1 publication Critical patent/ES2405155B1/es
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • B64C3/182—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
    • B64C1/064—Stringers; Longerons
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/26—Construction, shape, or attachment of separate skins, e.g. panels
    • 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
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/24—Structurally defined web or sheet [e.g., overall dimension, etc.]
    • Y10T428/24479—Structurally defined web or sheet [e.g., overall dimension, etc.] including variation in thickness
    • Y10T428/2457—Parallel ribs and/or grooves

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Laminated Bodies (AREA)
  • Moulding By Coating Moulds (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

Zonas de terminación de larguerillos optimizadas en componentes de aeronaves. Están dispuestas en un panel (11) de un material compuesto formado por un revestimiento (13) y al menos un larguerillo (15) de refuerzo configurado por un alma (17) y un pie (19) unido a dicho revestimiento (13); teniendo el larguerillo (15) una zona de terminación dentro de dicho panel sometida a un alto nivel de carga; teniendo el larguerillo (15) un alma (17) de altura decreciente en dicha zona de terminación y un pie (19) con una primera sección (31) de ancho variable desde un valor inicial W1 a un valor final W2 y una segunda sección (33) con una anchura W2 en dicha zona de terminación; teniendo el pie (19) y el alma (17) de dicho larguerillo (15) un espesor decreciente en dicha zona de terminación para mejorar la transferencia de carga desde el larguerillo (15) al revestimiento (13).
ES201131711A 2011-10-24 2011-10-24 Zonas de terminación de larguerillos optimizadas en componentes de aeronaves Active ES2405155B1 (es)

Priority Applications (3)

Application Number Priority Date Filing Date Title
ES201131711A ES2405155B1 (es) 2011-10-24 2011-10-24 Zonas de terminación de larguerillos optimizadas en componentes de aeronaves
US13/608,509 US20130101801A1 (en) 2011-10-24 2012-09-10 Optimized stringer run-out zones in aircraft components
PCT/ES2012/070733 WO2013060916A1 (es) 2011-10-24 2012-10-22 Componentes de aeronaves con zonas de terminación de larguerillos optimizadas

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
ES201131711A ES2405155B1 (es) 2011-10-24 2011-10-24 Zonas de terminación de larguerillos optimizadas en componentes de aeronaves

Publications (3)

Publication Number Publication Date
ES2405155A2 ES2405155A2 (es) 2013-05-30
ES2405155R1 true ES2405155R1 (es) 2013-10-14
ES2405155B1 ES2405155B1 (es) 2014-09-02

Family

ID=47429843

Family Applications (1)

Application Number Title Priority Date Filing Date
ES201131711A Active ES2405155B1 (es) 2011-10-24 2011-10-24 Zonas de terminación de larguerillos optimizadas en componentes de aeronaves

Country Status (3)

Country Link
US (1) US20130101801A1 (es)
ES (1) ES2405155B1 (es)
WO (1) WO2013060916A1 (es)

Families Citing this family (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8974886B2 (en) * 2012-04-25 2015-03-10 The Boeing Company Disbond resistant composite stiffener runout
US9527575B2 (en) * 2012-11-26 2016-12-27 The Boeing Company Multi-box wing spar and skin
ES2819076T3 (es) 2013-04-30 2021-04-14 Airbus Operations Sl Estructura compuesta para una aeronave y procedimiento de fabricación de la misma
US10479475B2 (en) 2013-08-09 2019-11-19 The Boeing Company Composite stringer beam joint structure of an aircraft
US10086922B2 (en) * 2013-11-15 2018-10-02 The Boeing Company Low stress stiffener runout in Pi bonded structure
CN106986046B (zh) * 2017-04-19 2019-09-03 北京猎鹰无人机科技有限公司 网状机翼的制作方法
GB2565350A (en) 2017-08-11 2019-02-13 Airbus Operations Ltd Panel assembly
EP3486074B1 (en) * 2017-11-15 2024-04-03 Airbus Operations S.L. Composite structure having an integrated support, attachable system comprising the composite structure, and method for manufacturing said composite structure
US11180238B2 (en) * 2018-11-19 2021-11-23 The Boeing Company Shear ties for aircraft wing
US10919256B2 (en) * 2019-05-09 2021-02-16 The Boeing Company Composite structure having a variable gage and methods for forming a composite structure having a variable gage
US10919260B2 (en) * 2019-05-09 2021-02-16 The Boeing Company Composite structure having a variable gage and methods for forming a composite structure having a variable gage
US10913215B2 (en) * 2019-05-09 2021-02-09 The Boeing Company Composite structure having a variable gage and methods for forming a composite structure having a variable gage

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102007033868A1 (de) * 2007-07-20 2009-01-22 Airbus Deutschland Gmbh Profil mit wenigstens einem Hohlprofilabschnitt
US20100170985A1 (en) * 2007-06-29 2010-07-08 Airbus Uk Limited Composite panel stiffener
WO2011003844A2 (en) * 2009-07-10 2011-01-13 Airbus Operations Limited Stringer
US20110174927A1 (en) * 2010-01-15 2011-07-21 Airbus Operations, S.L. Aircraft component with panels stiffened with stringers

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2866626B1 (fr) 2004-02-20 2006-05-19 Airbus France Arret de raidisseur a pentes decalees et panneau muni d'un tel arret
GB0708333D0 (en) 2007-04-30 2007-06-06 Airbus Uk Ltd Composite structure

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100170985A1 (en) * 2007-06-29 2010-07-08 Airbus Uk Limited Composite panel stiffener
DE102007033868A1 (de) * 2007-07-20 2009-01-22 Airbus Deutschland Gmbh Profil mit wenigstens einem Hohlprofilabschnitt
WO2011003844A2 (en) * 2009-07-10 2011-01-13 Airbus Operations Limited Stringer
US20110174927A1 (en) * 2010-01-15 2011-07-21 Airbus Operations, S.L. Aircraft component with panels stiffened with stringers

Also Published As

Publication number Publication date
WO2013060916A9 (es) 2014-04-17
US20130101801A1 (en) 2013-04-25
ES2405155B1 (es) 2014-09-02
ES2405155A2 (es) 2013-05-30
WO2013060916A1 (es) 2013-05-02

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