WO2009003954A1 - Cover for an aircraft access opening - Google Patents
Cover for an aircraft access opening Download PDFInfo
- Publication number
- WO2009003954A1 WO2009003954A1 PCT/EP2008/058305 EP2008058305W WO2009003954A1 WO 2009003954 A1 WO2009003954 A1 WO 2009003954A1 EP 2008058305 W EP2008058305 W EP 2008058305W WO 2009003954 A1 WO2009003954 A1 WO 2009003954A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- cover
- skin
- composite material
- access opening
- aircraft structure
- Prior art date
Links
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
- B64C1/1407—Doors; surrounding frames
- B64C1/1446—Inspection hatches
-
- 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
Definitions
- the present invention relates to a cover for an access opening in a composite material aircraft structure.
- the access openings for aircraft fuel tanks and the covers of said access openings in aeronautical structures are necessary for both the assembly and subsequent aircraft maintenance and inspection tasks, during the entire life of such aircraft.
- the requirements of these accesses vary according to the type of access which they must allow and to the frequency of their use.
- access covers which must comply with the following requirements: - the size must be appropriate to the accessibility requirements; the cover must be sealed for the purpose of preventing fuel losses; the impact requirements must be complied with; - the covers must be assembled and disassembled as quickly and easily as possible; the covers must be exchangeable.
- the present invention is aimed at satisfying this demand.
- the present invention relates to a cover for the access opening in a composite material aircraft structure, particularly made of carbon fiber.
- This type of covers is mainly used in aircraft stabilizers and wings, typically in fuel tank areas, and allows the complete access by the entire body of a person to the inner structure of the aircraft component in question.
- the type of cover for the access opening in a composite material aircraft structure comprises the following elements: an outer and an inner cover; an adjusting washer between the inner cover and the skin; sealing profiles between the inner cover and the adjusting washer and between the outer cover and the skin; a plate between the skin and the outer cover.
- Figure 1 shows a cover for the access opening of a known metallic aircraft structure.
- Figure 2 shows a detail of the installation of a cover for the access opening of a known metallic aircraft structure.
- Figure 3 shows a cover for the access opening of a known composite material aircraft structure.
- Figure 4 shows a detail of the installation of a cover for the access opening of a known composite material aircraft structure .
- Figure 5 shows the deformation of composite material layers for the adaptation to the aircraft structure surface in the installation of a cover for the access opening of a composite material aircraft structure according to the invention.
- Figure 6 shows in detail the plate used to install a cover for the access opening of a composite material aircraft structure according to the invention.
- Figure 7 shows a detail of the line of the access openings and the arrangement of the plate of a cover for the access opening of a composite material aircraft structure according to the invention.
- Figure 8 shows in detail the adjusting washer of a cover for the access opening of a composite material aircraft structure according to the invention.
- Figure 9 shows a detail of the arrangement of the adjusting washer of a cover for the access opening of a composite material aircraft structure according to the invention.
- Figure 10 shows a detail of the assembly of the cover for the access opening of a composite material aircraft structure according to the invention.
- Figure 11 shows an exploded view of the cover for the access opening of a composite material aircraft structure according to the invention.
- one of the typically used solutions for the access opening covers of metallic aircraft structures comprises two separate covers, an inner cover 1 and an outer cover 2, the inner cover 1 being located inside the fuel tank, and the outer cover 2 being located on the aerodynamic surface.
- the covers 1 and 2 are arranged together by means of screwing, comprising between them the metallic skin panel 3.
- the closing sealing profiles 4 are arranged at the ends of the covers 1 and 2.
- a cavity 5 is machined in the outer face of the skin 3, to install the outer cover 2.
- the type of access opening cover thus comprises the following elements: - an inner cover 7 screwed to the skin 8 of the composite material aircraft structure by means of countersunk-head screws 9, a sealing profile 10 between the inner cover 7 and an adjusting washer 11 occasionally being necessary to prevent leakages; - an adjusting washer 111 secured to the inner face of the skin 8 to obtain the suitable planar surface for the correct seating of the cover; an outer plate 12, screwed to the inner cover 7, conferring the necessary aerodynamic surface to the assembly; electrical ground connections 13.
- the main problem to be solved upon adapting the cover to the fiber skin is the manner of arranging the outer cover inside the aerodynamic contour of the stabilizer or wing profile, taking into consideration, as has been mentioned, that carbon fiber is not easy to machine.
- the solution set forth by the present invention comprises the inclusion of the cavity 5 described in metallic structures ( Figures 1 and 2) in its original form, modifying the design and the process for manufacturing the skin 28 so as to adapt it to the new cover.
- the carbon fiber layers 14 are thus deformed towards the inner part of the torsion box, leaving enough space between the aerodynamic surface and the outer face of the skin 28 for the seating of the cover 18 (see Figure 5) .
- a carbon fiber plate 15 can be cured together with the base of skin 28 to cover these areas. As the access openings are usually not insulated, and a complete line along the stabilizer or wing span is usually necessary, a continuous plate 15 must be extended along the line of the access openings.
- the inner face of the skins 28 of a torsion box are usually stiffened by means of installing stringers 16.
- the separation between these stiffening elements 16 is normally optimized for a specific typology.
- the most extreme and complicated case, which occurs when the separation between the stringers 16 is so small that the distance between the access opening and the foot of the stringer 19 is very small or even nil, has been considered in order to develop the invention. In this case, it is necessary to install an adjusting washer 31 to achieve a correct seating of the inner cover 27.
- the adjusting washer 31 may not be placed, if the inner face is sufficiently planar and allows a correct seating of the cover.
- a sealing profile 30 may be placed between this adjusting washer 31 and the inner cover 27, to thus ensure the sealing and prevent any leakage. If a double sealing is necessary, a second profile sealing 17 can be installed in the outer cover 18.
- the cover for the access opening in a composite material aircraft structure comprises the following elements as a whole: outer 18 and inner 27 cover; adjusting washer 31; - sealing profiles (not shown) ; plate 15.
Abstract
Description
Claims
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
AT08774466T ATE555010T1 (en) | 2007-06-29 | 2008-06-27 | COVER FOR AN AIRCRAFT ACCESS OPENING |
EP08774466A EP2170697B1 (en) | 2007-06-29 | 2008-06-27 | Cover for an aircraft access opening |
BRPI0813458-8A2A BRPI0813458A2 (en) | 2007-06-29 | 2008-06-27 | COVERAGE FOR AN AIRPLANE ACCESS OPENING |
CA2692291A CA2692291C (en) | 2007-06-29 | 2008-06-27 | Cover for an aircraft access opening |
RU2010102908/11A RU2469908C2 (en) | 2007-06-29 | 2008-06-27 | Aircraft access hole cover |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
ES200701834A ES2335837B1 (en) | 2007-06-29 | 2007-06-29 | COVER FOR AIRCRAFT ACCESS MOUTH. |
ESP200701834 | 2007-06-29 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2009003954A1 true WO2009003954A1 (en) | 2009-01-08 |
Family
ID=39967759
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/EP2008/058305 WO2009003954A1 (en) | 2007-06-29 | 2008-06-27 | Cover for an aircraft access opening |
Country Status (8)
Country | Link |
---|---|
US (1) | US8016235B2 (en) |
EP (1) | EP2170697B1 (en) |
AT (1) | ATE555010T1 (en) |
BR (1) | BRPI0813458A2 (en) |
CA (1) | CA2692291C (en) |
ES (1) | ES2335837B1 (en) |
RU (1) | RU2469908C2 (en) |
WO (1) | WO2009003954A1 (en) |
Cited By (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
WO2011099275A1 (en) * | 2010-02-10 | 2011-08-18 | 三菱航空機株式会社 | Closure member for opening |
WO2011099274A1 (en) * | 2010-02-10 | 2011-08-18 | 三菱航空機株式会社 | Closure member for opening |
WO2012024051A1 (en) * | 2010-08-17 | 2012-02-23 | The Boeing Company | Multi-spar port box joint |
FR2966424A1 (en) * | 2010-10-26 | 2012-04-27 | Airbus Operations Sas | AIRCRAFT PANEL COMPRISING AN OPENING EQUIPPED WITH A FRAMEWORK |
EP2492200A3 (en) * | 2011-02-24 | 2016-03-09 | Airbus Operations Limited | An aircraft fuel tank access cover and an aircraft fuel tank |
EP2487106A4 (en) * | 2009-10-08 | 2017-06-07 | Mitsubishi Heavy Industries, Ltd. | Composite material structure, as well as aircraft wing and fuselage provided therewith |
Families Citing this family (22)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
ES2347507B1 (en) * | 2007-12-27 | 2011-08-17 | Airbus Operations, S.L. | OPTIMIZED AIRCRAFT ACCESS MOUTH. |
ES2383863B1 (en) | 2009-05-06 | 2013-06-10 | Airbus Operations, S.L. | COMPOSITE MATERIAL PART WITH GREAT THICKNESS CHANGE. |
US8443575B1 (en) | 2009-10-27 | 2013-05-21 | The Boeing Company | Composite access door |
ES2396508B1 (en) * | 2010-10-13 | 2014-02-12 | Airbus Operations, S.L. | RAYS PROTECTION SYSTEM FOR AIRCRAFT ACCESS COVERS. |
ES2404456B1 (en) * | 2011-01-26 | 2014-04-29 | Airbus Operations S.L. | ASSEMBLY OF AN ACCESS MOUTH IN THE LOWER COATING OF AN AIRCRAFT WING MADE WITH A COMPOSITE MATERIAL. |
WO2013109305A1 (en) | 2011-08-19 | 2013-07-25 | Aerovironment, Inc. | Water-tight compartment with removable hatch and two-sided gel seal for multiple conduit access |
BRPI1105342B1 (en) * | 2011-12-28 | 2020-12-01 | Embraer S.A. | structural arrangement for fuel tank access window with composite coating |
JP5875377B2 (en) * | 2012-01-13 | 2016-03-02 | 三菱航空機株式会社 | Aircraft fuselage |
US9016631B2 (en) * | 2012-04-09 | 2015-04-28 | R4 Integration, Inc. | Multi-purpose hatch system |
EP2664547B1 (en) * | 2012-05-16 | 2016-04-06 | Airbus Operations, S.L. | Outer fuel tank access cover, wing and aircraft |
EP2842865B1 (en) * | 2013-08-28 | 2019-12-18 | Airbus Operations GmbH | Window panel for an airframe and method of producing same |
US9611028B2 (en) * | 2014-01-17 | 2017-04-04 | William J. Boyer | Pressure relief panel guard |
US9517830B2 (en) * | 2014-03-18 | 2016-12-13 | The Boeing Company | Seal design for vehicle and structure application |
US9718533B2 (en) * | 2014-07-01 | 2017-08-01 | Textron Innovations, Inc. | Fuel tank access door systems and methods |
US10207789B2 (en) | 2016-08-16 | 2019-02-19 | The Boeing Company | Aircraft composite wingbox integration |
US10421528B2 (en) * | 2016-08-16 | 2019-09-24 | The Boeing Company | Planked stringers that provide structural support for an aircraft wing |
US10364039B2 (en) * | 2017-04-25 | 2019-07-30 | Bell Helicopter Textron Inc. | Deformable clips for an aircraft fuel systems |
US10850858B2 (en) * | 2017-06-28 | 2020-12-01 | Textron Innovations Inc. | Breakaway cover for emergency access |
US11014678B2 (en) * | 2018-04-25 | 2021-05-25 | Roberto Antonio Ogarrio | Aircraft window plug device |
RU2715249C1 (en) * | 2019-07-30 | 2020-02-26 | Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") | Helicopter stabilizer |
RU194817U1 (en) * | 2019-09-12 | 2019-12-24 | Публичное акционерное общество (ПАО) "Туполев" | HATCH COVER ASSEMBLY IN THE CESSON OF THE AIRCRAFT WING AND HATCH PANEL |
CN111924113A (en) * | 2020-09-15 | 2020-11-13 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | Structure of fuel tank opening cover and peripheral area of opening cover of airplane wing |
Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2576734A (en) | 1949-07-29 | 1951-11-27 | Republic Aviat Corp | Access door and method of making and mounting the same |
US4291816A (en) | 1980-07-09 | 1981-09-29 | Canadair Limited | Fuel tank access door for aircraft |
US4579248A (en) | 1983-11-10 | 1986-04-01 | The Boeing Company | Access panel assembly for aircraft fuel tank |
WO2003022678A1 (en) | 2001-07-21 | 2003-03-20 | Bae Systems Plc | Aircraft structural components |
US20050121554A1 (en) | 2003-12-04 | 2005-06-09 | Ludovic Fournie | Device for equipping a hole in a panel, and panel thus equipped |
Family Cites Families (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2293656A (en) * | 1942-01-03 | 1942-08-18 | Lockheed Aircraft Corp | Transparent closure and mounting |
DE1252533B (en) * | 1965-11-10 | |||
SU942350A1 (en) * | 1981-01-04 | 2004-12-10 | А.Л. Доброскоков | DOOR HATCH |
US4541595A (en) * | 1983-03-28 | 1985-09-17 | Heath-Tecna Precision Structures | Removable interior window unit for aircraft |
US5014934A (en) * | 1989-06-30 | 1991-05-14 | The Boeing Company | Removable seal for discontinuities in aircraft skin |
US6889937B2 (en) * | 1999-11-18 | 2005-05-10 | Rocky Mountain Composites, Inc. | Single piece co-cure composite wing |
US6964723B2 (en) * | 2002-10-04 | 2005-11-15 | The Boeing Company | Method for applying pressure to composite laminate areas masked by secondary features |
US7300693B2 (en) * | 2003-09-04 | 2007-11-27 | The Boeing Company | Resin infused transparent skin panel and method of making same |
-
2007
- 2007-06-29 ES ES200701834A patent/ES2335837B1/en not_active Expired - Fee Related
- 2007-08-28 US US11/897,007 patent/US8016235B2/en not_active Expired - Fee Related
-
2008
- 2008-06-27 EP EP08774466A patent/EP2170697B1/en not_active Not-in-force
- 2008-06-27 RU RU2010102908/11A patent/RU2469908C2/en not_active IP Right Cessation
- 2008-06-27 WO PCT/EP2008/058305 patent/WO2009003954A1/en active Application Filing
- 2008-06-27 BR BRPI0813458-8A2A patent/BRPI0813458A2/en not_active IP Right Cessation
- 2008-06-27 CA CA2692291A patent/CA2692291C/en not_active Expired - Fee Related
- 2008-06-27 AT AT08774466T patent/ATE555010T1/en active
Patent Citations (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2576734A (en) | 1949-07-29 | 1951-11-27 | Republic Aviat Corp | Access door and method of making and mounting the same |
US4291816A (en) | 1980-07-09 | 1981-09-29 | Canadair Limited | Fuel tank access door for aircraft |
US4579248A (en) | 1983-11-10 | 1986-04-01 | The Boeing Company | Access panel assembly for aircraft fuel tank |
WO2003022678A1 (en) | 2001-07-21 | 2003-03-20 | Bae Systems Plc | Aircraft structural components |
US20050121554A1 (en) | 2003-12-04 | 2005-06-09 | Ludovic Fournie | Device for equipping a hole in a panel, and panel thus equipped |
Cited By (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2487106A4 (en) * | 2009-10-08 | 2017-06-07 | Mitsubishi Heavy Industries, Ltd. | Composite material structure, as well as aircraft wing and fuselage provided therewith |
US8752792B2 (en) | 2010-02-10 | 2014-06-17 | Mitubishi Aircarft Corporation | Closing member for opening |
JP2011162082A (en) * | 2010-02-10 | 2011-08-25 | Mitsubishi Aircraft Corp | Closure member for opening part |
JP2011162081A (en) * | 2010-02-10 | 2011-08-25 | Mitsubishi Aircraft Corp | Closure member for opening part |
WO2011099275A1 (en) * | 2010-02-10 | 2011-08-18 | 三菱航空機株式会社 | Closure member for opening |
US8840068B2 (en) | 2010-02-10 | 2014-09-23 | Mitsubishi Aircraft Corporation | Closing member for opening |
WO2011099274A1 (en) * | 2010-02-10 | 2011-08-18 | 三菱航空機株式会社 | Closure member for opening |
WO2012024051A1 (en) * | 2010-08-17 | 2012-02-23 | The Boeing Company | Multi-spar port box joint |
CN103097240A (en) * | 2010-08-17 | 2013-05-08 | 波音公司 | Multi-spar port box joint |
US8517312B2 (en) | 2010-08-17 | 2013-08-27 | The Boeing Company | Multi-spar port box joint |
FR2966424A1 (en) * | 2010-10-26 | 2012-04-27 | Airbus Operations Sas | AIRCRAFT PANEL COMPRISING AN OPENING EQUIPPED WITH A FRAMEWORK |
EP2447151A1 (en) * | 2010-10-26 | 2012-05-02 | Airbus Operations (S.A.S.) | Aircraft panel comprising an opening equipped with a surround |
US9132906B2 (en) | 2010-10-26 | 2015-09-15 | Airbus Operations S.A.S. | Aircraft panel comprising an opening equipped with a surround |
EP2492200A3 (en) * | 2011-02-24 | 2016-03-09 | Airbus Operations Limited | An aircraft fuel tank access cover and an aircraft fuel tank |
Also Published As
Publication number | Publication date |
---|---|
CA2692291A1 (en) | 2009-01-08 |
ES2335837A1 (en) | 2010-04-05 |
EP2170697A1 (en) | 2010-04-07 |
ES2335837B1 (en) | 2011-02-18 |
ATE555010T1 (en) | 2012-05-15 |
US20090294591A1 (en) | 2009-12-03 |
US8016235B2 (en) | 2011-09-13 |
RU2469908C2 (en) | 2012-12-20 |
BRPI0813458A2 (en) | 2014-12-23 |
EP2170697B1 (en) | 2012-04-25 |
RU2010102908A (en) | 2011-08-10 |
CA2692291C (en) | 2014-07-29 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US8016235B2 (en) | Cover for an aircraft access opening | |
RU2482996C2 (en) | Optimised aircraft hatch | |
US8662451B2 (en) | Manhole assembly in the lower skin of an aircraft wing made of a composite material | |
EP2441678B1 (en) | Lightning strike protection in aircraft | |
CN102245473B (en) | Overpressure hatch intended to be mounted on wall of turbojet engine nacelle | |
RU2531113C2 (en) | Cap, fastening structure using this cap, and aircraft comprising fastening structure | |
US8443575B1 (en) | Composite access door | |
US9248900B2 (en) | Tip fairing of a horizontal airfoil of an aircraft | |
US4291816A (en) | Fuel tank access door for aircraft | |
US8993090B2 (en) | Part for and method of repairing a damaged structure, in particular an airframe skin, and a repair kit for implementing it | |
US20100061031A1 (en) | Protection Device against Electrical Discharges in Aircraft | |
EA011137B1 (en) | Sealing system for the gap existing between the fuselage and the elevator of the orientable horizontal stabiliser of an aircraft, extended with an aerodynamic fairing for sealing of the opening existing between the fuselage and the orientable horizontal stabiliser | |
CN101512212A (en) | Method for manufacturing a panel assembly | |
US10889386B2 (en) | Device for electrically grounding aircraft components mounted on a composite skin fuselage | |
US9079656B2 (en) | Mistake resistant design for wing fuel tank access door alignment features | |
EP1857359B1 (en) | Sealing system for the gap existing between the fuselage and the elevator of an aircraft with orientable horizontal stabiliser | |
US9415855B2 (en) | Wing panel for aircraft | |
EP2465776B1 (en) | Lightning and corrosion protection arrangement in an aircraft structural component | |
RU2617905C2 (en) | Method to optimize access doors holes design at aircraft | |
EP4234410A1 (en) | Tank wall liner, tank and aircraft employing said tank wall liner and associated manufacturing methods |
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: 08774466 Country of ref document: EP Kind code of ref document: A1 |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2692291 Country of ref document: CA |
|
NENP | Non-entry into the national phase |
Ref country code: DE |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2008774466 Country of ref document: EP |
|
WWE | Wipo information: entry into national phase |
Ref document number: 2010102908 Country of ref document: RU |
|
ENP | Entry into the national phase |
Ref document number: PI0813458 Country of ref document: BR Kind code of ref document: A2 Effective date: 20091229 |