WO2007110586A1 - Aircraft component - Google Patents
Aircraft component Download PDFInfo
- Publication number
- WO2007110586A1 WO2007110586A1 PCT/GB2007/000977 GB2007000977W WO2007110586A1 WO 2007110586 A1 WO2007110586 A1 WO 2007110586A1 GB 2007000977 W GB2007000977 W GB 2007000977W WO 2007110586 A1 WO2007110586 A1 WO 2007110586A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- connector
- component
- arm
- connectors
- line
- Prior art date
Links
Classifications
-
- 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
- B64C3/18—Spars; Ribs; Stringers
Definitions
- the present invention relates to an aircraft component, a method of manufacturing an aircraft component, and a connector for transferring load between the body of an aircraft component and a cover.
- the connector may be, for example, a rib foot for transferring load between a wing skin and a wing rib.
- a rib foot of an aircraft wing rib is described in WO 01/76943.
- the rib foot has a pair of flanges, each having a pair of guide holes which have been drilled in the final locations of the final assembly holes, used for securing the wing skin.
- a first aspect of the invention provides a method of manufacturing an aircraft component, the method comprising:
- each connector having an arm extending from the body, a first flange positioned on a first side of the line and a second flange positioned on a second side of the line;
- the separate connector having an arm extending from the body, a first flange positioned on a first side of the line, and a second flange positioned on a second side of the line.
- the method of the first aspect of the invention enables the separate connector to be attached close to an adjacent connector in the line, whilst reducing the chance of a crack propagating between them, hi the event of failure of the separate connector, by positioning the flanges on opposite sides of the line, load will be transferred in a symmetrical manner to the remaining connectors.
- a second aspect of the invention provides an aircraft component comprising a body; and a series of connectors arranged in a line on the body, each connector having an arm extending from the body, a first flange positioned on a first side of the line and a second flange positioned on a second side of the line, wherein at least one of the connectors is a separate connector which has been attached to the body.
- the component can be fastened to a cover by welding, or more preferably by passing fastening elements (such as bolts) through the flanges of the connectors and through the cover,
- the cover is typically an element having an aerodynamic external surface, such as a fuselage skin or wing skin.
- the cover has an internal surface carrying a plurality of strengtheners, each strengthener being received in a channel between a pair of the connectors.
- the connectors and the cover may be formed from different materials, such as metal and composite respectively.
- the arm of the separate connector overlaps the arm of an adjacent connector when viewed from a side of the line.
- This provides a compact arrangement, and enables the arm of the separate connector and/or the arm of the adjacent connector to be provided with a strengthening portion which overlaps the other arm when viewed from a side of the line.
- the strengthening portion has an angled edge, to increase its bending stiffness.
- the arm of the separate connector has a relatively wide base adjacent to the body and a relatively narrow distal end which carries the flanges. This also increases the bending stiffness of the arm.
- each flange has one or more fastening holes for receiving a fastening element.
- the flanges of the separate connector, and of an adjacent connector have fewer holes than the other connectors in the line.
- At least one of the connectors is formed integrally with the body.
- a strengthener such as a ridge, may extend along the body adjacent to the connectors.
- the separate connector is typically secured to the body on a far side of the strengthenener.
- a third aspect of the invention provides a connector for transferring load between the body of an aircraft component and a cover, the cover having an aerodynamic external surface, the connector comprising:
- a plate for securing the connector to the body of the aircraft component having a first face on a first side of the connector, a second face on a second side of the connector, and an edge between the first and second faces;
- the arm has a relatively wide base adjacent to the edge of the plate and a relatively narrow distal end which carries the flanges.
- the symmetrical structure of the connector makes it suitable for use in the method of the first aspect of the invention.
- the plate may be welded to the body, but more preferably the plate has two or more fastening holes for receiving fastening elements (such as bolts).
- FIG. 1 is a plan view of an aircraft
- FIG. 2 is a view of part of a machined face of a wing rib
- FIG. 3 is an enlarged view of part of the opposite face of the wing rib
- FIG. 4 shows a separate bolted on part
- FIG. 5 is an enlarged view of part of the machined face of the wing rib with the bolted on part removed;
- FIG. 6 is a view of the complete wing rib and a wing skin
- FIG. 7 is an enlarged view of the wing rib and wing skin, showing the two-part rib foot in detail.
- Figure 1 shows an aircraft 1 with a fuselage 2 and a pair of wings each having a wing tip 3.
- Each wing has a pair of spars (not shown) attached to the fuselage and extending spanwise. Twenty four ribs (not shown) extend chordwise.
- Flaps 4 are mounted at the trailing edge of each wing. The flaps are carried by four flap attachments (not shown) each of which is secured to a respective rib.
- Each wing carries a pair of engines 5, and each engine is connected via a support structure (not shown) to a respective rib.
- Figure 2 shows a machined face of one of the ribs 10 with the fore and aft edges of the rib omitted.
- the rib 10 is machined from an Aluminium billet to form a number of vertical stiffeners 11; a lower boom ridge 12 and an upper boom ridge 13; and horizontal stiffeners 14.
- Fuel system holes 15 are formed to accommodate fuel system pipes.
- Holes 16 are formed in the intra-rib webs in order to reduce the weight of the rib.
- a flap track attachment 17 is formed with vertical stiffeners 18.
- the upper and lower edges of the rib 10 each carry a series of integral rib feet 19, arranged in a line along the rib.
- the upper edge of the rib also carries a two-part rib foot 20 in accordance with one embodiment of the invention, arranged in line with the integral rib feet.
- the rib feet 19 and 20 transfer load between the body of the rib and the wing skin.
- Figure 3 shows the two-part rib foot 20 and an adjacent integral rib foot 19 in detail.
- Figure 3 shows the opposite side of the rib to the side shown in Figure 2.
- Figure 3 also shows an aft edge 21 of the rib 10 which is attached to an aft spar (not shown).
- the integral rib foot 19 is machined from the same piece of Aluminium as the rest of the rib, and comprises an arm 22 extending from the upper edge of the rib, a first flange 23a carried by the arm on a first side of the rib, and a second flange 23b carried by the arm on a second side of the rib.
- the flanges 23a, 23b are formed with a pair of bolt holes 24a, 24b at one end and a pair of bolt holes 25a,25b at the other end.
- the integral rib foot 19 is separated from adjacent rib feet by a pair of U-shaped channels 26. Thus the rib feet exhibit a castellated appearance when viewed from the left or right-hand sides of the rib.
- the two-part rib foot 20 comprises a separate bolted on part 30 shown in detail in Figure 4, and an integrally formed part 40 shown in detail in Figure 5.
- the bolted on part 30 comprises a vertical plate 31 with ten bolt holes 32.
- the plate 31 is formed with a recess 33 to provide clearance for a hole 16 as shown in Figure 3.
- the plate 31 is fastened to the rib 10 by bolts (not shown) passing through bolt holes 34 in the rib (the bolt holes 34 being shown in Figure 5).
- An arm 35 extends from the upper edge of the plate 31.
- the arm 35 When viewed side-on, the arm 35 has a relatively wide base adjacent to the plate 31, a relatively narrow distal end, a vertical edge 36 and a triangular strengthening portion with an angled edge 37.
- the distal end of the arm 35 carries a first flange 38a on a first side of the plate and a second flange 38b on the opposite side of the plate.
- the flanges 38a, 38b have bolt holes 39a, 39b respectively.
- the integrally formed part 40 shown in Figure 5 is machined from the same piece of Aluminium as the rest of the rib, and comprises a projecting arm 41 extending from the upper edge of the rib.
- the arm 40 carries a first flange 42a on a first side of the rib and a second flange 42b on the opposite side of the rib.
- the flanges 42a, 42b have bolt holes 43 a, 43b respectively.
- the arm 41 has a vertical edge 44 and a strengthening portion with an angled edge 45.
- Figure 6 is a view of the rib 10 attached to a wing skin 50.
- the wing skin 50 has an external surface (not visible in Figure 6) forming an aerodynamic outer surface of the wing, and an internal surface 51 carrying a series of stringers running spanwise along the wing.
- the stringers are T-shaped in cross section with the upright 52 of the T extending into the interior of the wing and lying in a U-shaped channel 26 between two rib feet, and the arms 53 of the T lying parallel with the inner surface 51 of the skin 50.
- Figure 7 shows in detail the two-part rib foot and two adjacent stringers. As shown in Figure 7, the stringer arms 53 have parallel sides between the ribs, but as they approach a rib they taper outwardly to form wide portions 54.
- Bolts pass through the rib feet, plates 55, the wide portions 54 of the stringer arms 53, and the skin 50.
- the wing skin 50 is formed from a composite material such as carbon-fibre reinforced plastic.
- the stringers are formed from a composite material such as carbon-fibre reinforced plastic.
- the fore and aft edges 21, 60 respectively of the rib are attached to fore and aft spars (not shown).
- a flap track attachment 70 is bolted onto the rib by means of bolts (not shown) passing through bolt holes 71.
- a pair of lugs (not shown) are bolted on one side to the flap track attachment 17, and on the other side to the bolted on flap track attachment 70. The weight of the flaps is transferred to the flap track attachments 17, 70 by the lugs.
- Forming the part 30 as a separate connector (instead of forming it integrally with the adjacent connector 40) enables it to be attached to the body of the rib close to the connector 40, whilst reducing or eliminating the chance of a crack propagating between them.
- the two-part rib foot 20 is designed to fail in a symmetrical manner. That is, if either the part 30 or 40 fails, then the remaining part has two bolts arranged symmetrically with respect to the fore-aft axis of the rib.
- This can be contrasted with an alternative nonsymmetrical construction in which the two bolts on one side of the rib are carried by a bolted on part, and the two bolts on the other side of the rib are carried by an integrally formed part.
- failure of one part would result in the remaining bolts being on one side of the rib only. This eccentricity would result in a moment about the rib, and consequent spanwise loading in the composite wing skin which can exceed the bearing strength of the wing skin.
- a further problem associated with composite wing skins is that the Aluminium rib feet to which they are attached have a different coefficient of thermal expansion relative to the composite wing skin. This results in differential expansion which places additional load on the joint.
- the symmetrical nature of the two-part rib foot 20 means that such loads are not only distributed equally on both sides of the line of rib feet in the event of failure, it also reduces the chordwise magnitude of the differential thermal expansion because the flanges
- Figure 7 shows the triangular strengthening portion of the arm 41 (with angled edge 45), and shows how the strengthening portion overlaps the adjacent arm 35 when viewed from the machined side of the rib.
- the strengthening portion increases the bending stiffness of the arm 41, and the overlap provides a compact arrangement.
- the stiffening portion of the arm 35 overlaps the other arm 41 as shown most clearly in Figure 3.
- the triangular shape of the strengthening portion gives high bending stiffness with relatively low weight.
Abstract
Description
Claims
Priority Applications (8)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN2007800114212A CN101410292B (en) | 2006-03-27 | 2007-03-21 | Aircraft component, aircraft structure and method for manufacturing the component and structure |
AT07732069T ATE508044T1 (en) | 2006-03-27 | 2007-03-21 | AIRCRAFT COMPONENT |
JP2009502187A JP4951059B2 (en) | 2006-03-27 | 2007-03-21 | Aircraft components |
CA2644539A CA2644539C (en) | 2006-03-27 | 2007-03-21 | Aircraft component |
EP07732069A EP1999013B1 (en) | 2006-03-27 | 2007-03-21 | Aircraft component |
DE602007014340T DE602007014340D1 (en) | 2006-03-27 | 2007-03-21 | AIRCRAFT COMPONENTS |
BRPI0709838-3A BRPI0709838A2 (en) | 2006-03-27 | 2007-03-21 | aircraft component |
US12/225,137 US8186622B2 (en) | 2006-03-27 | 2007-03-21 | Aircraft component |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GBGB0606079.2A GB0606079D0 (en) | 2006-03-27 | 2006-03-27 | Aircraft component |
GB0606079.2 | 2006-03-27 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2007110586A1 true WO2007110586A1 (en) | 2007-10-04 |
Family
ID=36384241
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/GB2007/000977 WO2007110586A1 (en) | 2006-03-27 | 2007-03-21 | Aircraft component |
Country Status (11)
Country | Link |
---|---|
US (1) | US8186622B2 (en) |
EP (1) | EP1999013B1 (en) |
JP (1) | JP4951059B2 (en) |
CN (1) | CN101410292B (en) |
AT (1) | ATE508044T1 (en) |
BR (1) | BRPI0709838A2 (en) |
CA (1) | CA2644539C (en) |
DE (1) | DE602007014340D1 (en) |
GB (1) | GB0606079D0 (en) |
RU (1) | RU2428353C2 (en) |
WO (1) | WO2007110586A1 (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2011500444A (en) * | 2007-10-23 | 2011-01-06 | エアバス オペレーションズ リミティド | Wing structure and method for manufacturing rib of wing structure |
EP3078585A1 (en) * | 2015-04-07 | 2016-10-12 | The Boeing Company | Rib structure and method of forming thereof |
GB2552207A (en) * | 2016-07-14 | 2018-01-17 | Gkn Aerospace Services Ltd | Rib manufacturing |
Families Citing this family (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
FR2916417B1 (en) * | 2007-05-23 | 2009-07-24 | Airbus France Sas | STRUCTURAL AIRCRAFT ELEMENT LOCATED AT THE INTERFACE BETWEEN A WING AND FUSELAGE |
US7975965B2 (en) * | 2008-05-13 | 2011-07-12 | The Boeing Company | Wing tip joint in airfoils |
DE102008041259B4 (en) * | 2008-08-14 | 2012-11-29 | Airbus Operations Gmbh | Adhesive holder for connecting a lightweight component |
ES2372828B1 (en) * | 2008-12-17 | 2012-12-13 | Airbus Operations, S.L. | RIB-HARDWARE. |
GB2466793B (en) * | 2009-01-07 | 2011-11-09 | Ge Aviat Systems Ltd | Composite spars |
GB201008186D0 (en) * | 2010-05-17 | 2010-06-30 | Airbus Operations Ltd | A structural assembly for an aircraft |
GB201110973D0 (en) * | 2011-06-28 | 2011-08-10 | Airbus Operations Ltd | Bracket |
US9010688B2 (en) * | 2012-02-07 | 2015-04-21 | The Boeing Company | Structural joint having continuous skin with inside and outside stringers |
EP2815958A1 (en) * | 2013-06-18 | 2014-12-24 | Airbus Operations GmbH | Structural member and associated method |
US9296466B2 (en) * | 2013-06-21 | 2016-03-29 | The Boeing Company | Symmetric wing rib with center plane fastened shear ties |
US10745103B2 (en) * | 2017-05-31 | 2020-08-18 | The Boeing Company | Aircraft, aircraft wings and associated shear ties |
CN108583848A (en) * | 2018-07-09 | 2018-09-28 | 中国商用飞机有限责任公司北京民用飞机技术研究中心 | A kind of curvilinear ribs edge strip, rib and wing with curvilinear ribs edge strip |
US11319051B2 (en) * | 2020-01-03 | 2022-05-03 | The Boeing Company | Stiffened composite ribs |
CN113547148B (en) * | 2021-06-30 | 2022-09-23 | 北京卫星制造厂有限公司 | Adjustable auxiliary machining supporting device and method for weak-rigidity sheet metal structural part |
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WO2004018183A1 (en) * | 2002-08-21 | 2004-03-04 | Bae Systems Plc | Method and tool for forming a bracket in composite material and bracket |
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GB2409443A (en) * | 2003-12-23 | 2005-06-29 | Airbus Uk Ltd | Rib for an aircraft and the manufacture thereof |
US7527222B2 (en) * | 2004-04-06 | 2009-05-05 | The Boeing Company | Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections |
US7159822B2 (en) * | 2004-04-06 | 2007-01-09 | The Boeing Company | Structural panels for use in aircraft fuselages and other structures |
US7134629B2 (en) * | 2004-04-06 | 2006-11-14 | The Boeing Company | Structural panels for use in aircraft fuselages and other structures |
GB2417228A (en) * | 2004-08-18 | 2006-02-22 | Airbus Uk Ltd | Aircraft wing |
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JP4657189B2 (en) * | 2006-11-02 | 2011-03-23 | 本田技研工業株式会社 | Airplane wing structure |
US7635106B2 (en) * | 2006-11-30 | 2009-12-22 | The Boeing Company | Composite shear tie |
US7721995B2 (en) * | 2006-12-13 | 2010-05-25 | The Boeing Company | Rib support for wing panels |
US7686251B2 (en) * | 2006-12-13 | 2010-03-30 | The Boeing Company | Rib support for wing panels |
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JP4990177B2 (en) * | 2008-02-14 | 2012-08-01 | 本田技研工業株式会社 | Airplane wing structure |
ES2372828B1 (en) * | 2008-12-17 | 2012-12-13 | Airbus Operations, S.L. | RIB-HARDWARE. |
-
2006
- 2006-03-27 GB GBGB0606079.2A patent/GB0606079D0/en not_active Ceased
-
2007
- 2007-03-21 CA CA2644539A patent/CA2644539C/en not_active Expired - Fee Related
- 2007-03-21 AT AT07732069T patent/ATE508044T1/en not_active IP Right Cessation
- 2007-03-21 JP JP2009502187A patent/JP4951059B2/en not_active Expired - Fee Related
- 2007-03-21 EP EP07732069A patent/EP1999013B1/en not_active Not-in-force
- 2007-03-21 RU RU2008137496/11A patent/RU2428353C2/en not_active IP Right Cessation
- 2007-03-21 BR BRPI0709838-3A patent/BRPI0709838A2/en not_active IP Right Cessation
- 2007-03-21 WO PCT/GB2007/000977 patent/WO2007110586A1/en active Application Filing
- 2007-03-21 DE DE602007014340T patent/DE602007014340D1/en active Active
- 2007-03-21 US US12/225,137 patent/US8186622B2/en active Active
- 2007-03-21 CN CN2007800114212A patent/CN101410292B/en not_active Expired - Fee Related
Patent Citations (4)
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EP0048191A1 (en) | 1980-09-09 | 1982-03-24 | Aerospatiale Societe Nationale Industrielle | Airship fuselage structure resistant to longitudinal cracks of the skin |
US5518208A (en) * | 1993-12-28 | 1996-05-21 | The Boeing Company | Optimum aircraft body frame to body skin shear tie installation pattern for body skin/stringer circumferential splices |
WO2001076943A1 (en) | 2000-04-06 | 2001-10-18 | Bae Systems Plc | Assembly method |
WO2004018183A1 (en) * | 2002-08-21 | 2004-03-04 | Bae Systems Plc | Method and tool for forming a bracket in composite material and bracket |
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2011500444A (en) * | 2007-10-23 | 2011-01-06 | エアバス オペレーションズ リミティド | Wing structure and method for manufacturing rib of wing structure |
EP3078585A1 (en) * | 2015-04-07 | 2016-10-12 | The Boeing Company | Rib structure and method of forming thereof |
US10196126B2 (en) | 2015-04-07 | 2019-02-05 | The Boeing Company | Rib structure and method of forming thereof |
GB2552207A (en) * | 2016-07-14 | 2018-01-17 | Gkn Aerospace Services Ltd | Rib manufacturing |
GB2552207B (en) * | 2016-07-14 | 2019-03-13 | Gkn Aerospace Services Ltd | Aircraft wing rib and cover assembly |
Also Published As
Publication number | Publication date |
---|---|
JP2009531224A (en) | 2009-09-03 |
RU2008137496A (en) | 2010-05-10 |
EP1999013A1 (en) | 2008-12-10 |
ATE508044T1 (en) | 2011-05-15 |
CA2644539C (en) | 2014-05-06 |
CN101410292B (en) | 2011-04-20 |
CA2644539A1 (en) | 2007-10-04 |
US8186622B2 (en) | 2012-05-29 |
RU2428353C2 (en) | 2011-09-10 |
US20090272848A1 (en) | 2009-11-05 |
CN101410292A (en) | 2009-04-15 |
GB0606079D0 (en) | 2006-05-03 |
JP4951059B2 (en) | 2012-06-13 |
BRPI0709838A2 (en) | 2011-07-26 |
EP1999013B1 (en) | 2011-05-04 |
DE602007014340D1 (en) | 2011-06-16 |
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