[go: up one dir, main page]

WO2015170090A1 - Réservoir de carburant d'aéronef - Google Patents

Réservoir de carburant d'aéronef Download PDF

Info

Publication number
WO2015170090A1
WO2015170090A1 PCT/GB2015/051323 GB2015051323W WO2015170090A1 WO 2015170090 A1 WO2015170090 A1 WO 2015170090A1 GB 2015051323 W GB2015051323 W GB 2015051323W WO 2015170090 A1 WO2015170090 A1 WO 2015170090A1
Authority
WO
WIPO (PCT)
Prior art keywords
tank wall
reinforcing member
tank
shaped cross
section
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.)
Ceased
Application number
PCT/GB2015/051323
Other languages
English (en)
Inventor
Andrew James IRWIN
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.)
BAE Systems PLC
Original Assignee
BAE Systems PLC
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
Priority claimed from EP14275106.4A external-priority patent/EP2942270A1/fr
Priority claimed from GBGB1408019.6A external-priority patent/GB201408019D0/en
Application filed by BAE Systems PLC filed Critical BAE Systems PLC
Publication of WO2015170090A1 publication Critical patent/WO2015170090A1/fr
Anticipated expiration legal-status Critical
Ceased legal-status Critical Current

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
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/34—Tanks constructed integrally with wings, e.g. for fuel or water
    • 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
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/02—Tanks
    • 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
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/02—Tanks
    • B64D37/06—Constructional adaptations thereof
    • 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
    • B64D37/00—Arrangements in connection with fuel supply for power plant
    • B64D37/32—Safety measures not otherwise provided for, e.g. preventing explosive conditions
    • B64D2037/325—Fuel tanks with provisions for reduction hydraulic ram shocks due to projectile impacts

Definitions

  • the reinforcing member is made of a metal or alloy.
  • the reinforcing member comprises a first portion and a second portion connected to the first portion and oblique to the first portion.
  • the first portion of the reinforcing member is fixedly attached to the first tank wall.
  • the second portion of the reinforcing member is fixedly attached to the second tank wall.
  • the metal or alloy reinforcing member tends to be more flexible and more ductile than the carbon composite tank walls. This tends to provide that, under, for example, hydrodynamic ram loads that would cause the carbon fibre composite tank walls to deform beyond normal design limits and break, the metal or alloy reinforcing member tends not to break, and instead flexes and bends, but remains complete.
  • the present invention provides a method of reinforcing an aircraft fuel tank in a wing of an aircraft.
  • the aircraft fuel tank comprises a plurality of tank walls enclosing a liquid storage space.
  • the plurality of tank walls include a first tank wall and a second tank wall.
  • the second tank wall is coupled to the first tank wall and is oblique to the first tank wall.
  • the first tank wall is formed by an external skin of the aircraft.
  • the second tank wall is formed by at least part of a rib or a spar of a substructure of the aircraft.
  • the first tank wall is made of a carbon fibre composite material.
  • the second tank wall is made of a carbon fibre composite material.
  • the second tank wall may have a substantially J-shaped cross section.
  • the reinforcing member may have a substantially L-shaped cross section.
  • the step of attaching together the second tank wall and the reinforcing member may form a member having a substantially I-shaped cross section.
  • the reinforcing member may be made of metal (e.g. aluminium).
  • the liquid storage tank may be an aircraft fuel tank on an aircraft.
  • the first tank wall may be formed from at least part of an external skin of the aircraft.
  • the second tank wall may be formed from at least part of a rib or a spar of a substructure of the aircraft.
  • Figure 1 is a schematic illustration (not to scale) of an exploded view of an example aircraft wing 2 in which an embodiment of a hydrodynamic ram reducing baffle is implemented.
  • the rib 8 and the reinforcing member 18 are fixedly attached together so as to form an assembly that, when viewed from the side as shown in Figure 2, has a substantially I-shaped cross-section.
  • the reinforcing member 8 and the second and third portions 8b, 8c of the rib 8 form an assembly having a generally T-shaped cross-section.
  • the second portion 18b of each reinforcing member 18 extends along at least a quarter of the length of the second portion 8b of the respective rib 8 to which it is attached.
  • the projectile 24 initially impacts with an external surface of the lower skin 12 and travels through the lower skin 12.
  • the projectile 24 causes high strain rate shear damage to the lower skin 12 resulting in a hole in the lower skin 12 approximately the size of the projectile 24.

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Cooling, Air Intake And Gas Exhaust, And Fuel Tank Arrangements In Propulsion Units (AREA)

Abstract

L'invention concerne un réservoir de carburant d'aéronef (16), comprenant : une pluralité de parois de réservoir entourant un espace de stockage de liquide (14), la pluralité de parois de réservoir comprenant une première paroi de réservoir (10) (par exemple, une enveloppe extérieure de l'aéronef) et une seconde paroi de réservoir (8) (par exemple, une nervure ou un longeron d'une sous-structure d'aéronef) accouplée à la première paroi de réservoir (10) et oblique par rapport à cette dernière ; et un élément de renforcement (18) comprenant une première partie (18a) et une seconde partie (18b) reliée à la première partie (18a) et oblique par rapport à cette dernière. La première partie (18a) de l'élément de renforcement (18) est attachée de façon fixe à la première paroi de réservoir (10), et la seconde partie (18b) de l'élément de renforcement (18) est attachée de façon fixe à la seconde paroi de réservoir (8), en s'opposant ainsi à un mouvement de la première paroi de réservoir (10) par rapport à la seconde paroi de réservoir (8).
PCT/GB2015/051323 2014-05-07 2015-05-06 Réservoir de carburant d'aéronef Ceased WO2015170090A1 (fr)

Applications Claiming Priority (4)

Application Number Priority Date Filing Date Title
EP14275106.4 2014-05-07
GB1408019.6 2014-05-07
EP14275106.4A EP2942270A1 (fr) 2014-05-07 2014-05-07 Réservoir de stockage de liquide
GBGB1408019.6A GB201408019D0 (en) 2014-05-07 2014-05-07 Liquid storage tank

Publications (1)

Publication Number Publication Date
WO2015170090A1 true WO2015170090A1 (fr) 2015-11-12

Family

ID=53276176

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/GB2015/051323 Ceased WO2015170090A1 (fr) 2014-05-07 2015-05-06 Réservoir de carburant d'aéronef

Country Status (2)

Country Link
GB (1) GB2528538A (fr)
WO (1) WO2015170090A1 (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109305328A (zh) * 2018-11-12 2019-02-05 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种翼盒及飞机
CN113415432A (zh) * 2021-07-30 2021-09-21 天津爱思达新材料科技有限公司 飞机副油箱安定面结构

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2604141A (en) * 2021-02-25 2022-08-31 Airbus Operations Ltd Aircraft wing with tubular fuel tanks

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19529476A1 (de) * 1995-08-11 1997-02-13 Deutsche Forsch Luft Raumfahrt Flügel mit schubsteifen Flügelschalen aus Faserverbundwerkstoffen für Luftfahrzeuge
US5934618A (en) * 1995-12-01 1999-08-10 The Boeing Company Passive dynamic structure damage control in a hydraulic ram environment
US20080023585A1 (en) * 2004-12-29 2008-01-31 Kordel Jan A Aircraft wing composed of composite and metal panels
WO2008067460A2 (fr) * 2006-11-30 2008-06-05 The Boeing Company Barre de cisaillement composite
US20100148008A1 (en) * 2008-12-17 2010-06-17 Airbus Espana, S.L. Rib-fitting

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB9024387D0 (en) * 1990-11-09 1991-01-02 British Aerospace Carbon fibre composite wing manufacture
US7575194B2 (en) * 2006-11-30 2009-08-18 The Boeing Company Apparatuses and methods for joining composite members and other structural members in aircraft wing boxes and other structures
FR2923800B1 (fr) * 2007-11-16 2010-05-21 Airbus France Dispositif de liaison entre une piece de structure interne d'un aeronef et le fuselage de celui-ci
DE102009033444A1 (de) * 2009-07-16 2011-01-27 Airbus Operations Gmbh Schalensegment zur Herstellung einer Rumpfzellensektion für eine Rumpfzelle eines Flugzeugs
US8578609B2 (en) * 2010-10-27 2013-11-12 Airbus Operations S.L. Manufacturing procedure of a part made out of a composite material introducing a geometric change in one of its faces

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19529476A1 (de) * 1995-08-11 1997-02-13 Deutsche Forsch Luft Raumfahrt Flügel mit schubsteifen Flügelschalen aus Faserverbundwerkstoffen für Luftfahrzeuge
US5934618A (en) * 1995-12-01 1999-08-10 The Boeing Company Passive dynamic structure damage control in a hydraulic ram environment
US20080023585A1 (en) * 2004-12-29 2008-01-31 Kordel Jan A Aircraft wing composed of composite and metal panels
WO2008067460A2 (fr) * 2006-11-30 2008-06-05 The Boeing Company Barre de cisaillement composite
US20100148008A1 (en) * 2008-12-17 2010-06-17 Airbus Espana, S.L. Rib-fitting

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109305328A (zh) * 2018-11-12 2019-02-05 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种翼盒及飞机
CN109305328B (zh) * 2018-11-12 2024-01-16 中国商用飞机有限责任公司北京民用飞机技术研究中心 一种翼盒及飞机
CN113415432A (zh) * 2021-07-30 2021-09-21 天津爱思达新材料科技有限公司 飞机副油箱安定面结构

Also Published As

Publication number Publication date
GB201507729D0 (en) 2015-06-17
GB2528538A (en) 2016-01-27

Similar Documents

Publication Publication Date Title
EP3140193B1 (fr) Réservoir de stockage de liquide
US8398021B2 (en) Compliant crown panel for an aircraft
CN104066647B (zh) 冲击抵抗和损坏容限改善的飞行器机身段
EP3140197B1 (fr) Système de stockage de liquide
EP3140195B1 (fr) Système de stockage de liquide
CN101786499A (zh) 抗冲击的飞行器前缘结构及具有该结构的飞行器
WO2015170090A1 (fr) Réservoir de carburant d'aéronef
US10086921B2 (en) Aircraft having a forward-facing section that deflects elastically under impact loads
EP3140196B1 (fr) Système de stockage de liquide
Morinière et al. Development of fibre-metal laminates for improved impact performance
EP2942270A1 (fr) Réservoir de stockage de liquide
EP2942281A1 (fr) Réservoir de stockage de liquide
EP2942283A1 (fr) Système de stockage de liquide
EP2942282A1 (fr) Système de stockage de liquide
EP2942278A1 (fr) Système de stockage de liquide
US20170043880A1 (en) Liquid storage system
EP2942280A1 (fr) Système de stockage de liquide
EP2942284A1 (fr) Réservoir de stockage de liquide et système de cloison
US20170050741A1 (en) Baffle
EP3140198B1 (fr) Réservoir d'aéronef et système de cloison
EP3838744A1 (fr) Bord d'attaque pour un profil aérodynamique
EP2942279A1 (fr) Paroi d'un réservoir ou d'un récipient destiné à contenir un fluide
US20130164484A1 (en) Lightweight impact resistant panel

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 15726249

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 15726249

Country of ref document: EP

Kind code of ref document: A1