GB615284A - Built-up laminar-flow aerofoil - Google Patents
Built-up laminar-flow aerofoilInfo
- Publication number
- GB615284A GB615284A GB22904/46A GB2290446A GB615284A GB 615284 A GB615284 A GB 615284A GB 22904/46 A GB22904/46 A GB 22904/46A GB 2290446 A GB2290446 A GB 2290446A GB 615284 A GB615284 A GB 615284A
- Authority
- GB
- United Kingdom
- Prior art keywords
- flanges
- panels
- edge portion
- aerofoil
- marginal flanges
- 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.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Connection Of Plates (AREA)
Abstract
615,284. Aerofoils. ARMSTRONG WHITWORTH AIRCRAFT, Ltd., SIR W. G., WOODHAMS, H. M., and LOCKWOOD, S. W. D. Aug. 1, 1946, Nos. 22904/46 and 16741/47. [Class 4] An aerofoil has at least the main portion of its air-swept surface formed of panels, of appropriate curvature, having inwardly projecting marginal flanges rigidly connected together by bolts, each of the panels being machined from a bar or plate of sufficient thickness for the formation of the marginal flanges. In the form shown in Fig. 1, upper and lower panels 21, 22 of light alloy are secured to spars 30, 31 and stiffeners 32 by bolts passing through spanwise flanges 25 and chordwise flanges 24 respectively. As shown in Fig. 3, the peripheral edges of the spars and stiffeners extend to the exterior surface of the aerofoil; alternatively, they may be recessed into the marginal flanges which are arranged to abut each other. The marginal flanges are stayed by triangular gussets 26, and the panels may also be provided with chordwise-extending reinforcing ridges between the flanges 24, also provided with similar gussets. The leading- edge portion 23 of the aerofoil is bolted to the spar 30, and the trailing-edge portion to the spar 31. Fig. 8 shows an alternative method of securing the leading-edge portion 37 in a recess 36 along the edge of the flange 25 to provide a flush joint. Such an arrangement may be used for attaching the trailing-edge portion, or for flush fitting access plates. The exterior surfaces of the panels are machined to the desired profile. Specification 615,275 is referred to in the first Provisional Specification.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB22904/46A GB615284A (en) | 1946-08-01 | 1946-08-01 | Built-up laminar-flow aerofoil |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB22904/46A GB615284A (en) | 1946-08-01 | 1946-08-01 | Built-up laminar-flow aerofoil |
Publications (1)
Publication Number | Publication Date |
---|---|
GB615284A true GB615284A (en) | 1949-01-04 |
Family
ID=10186940
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB22904/46A Expired GB615284A (en) | 1946-08-01 | 1946-08-01 | Built-up laminar-flow aerofoil |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB615284A (en) |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1371551A1 (en) * | 2002-06-12 | 2003-12-17 | Honda Giken Kogyo Kabushiki Kaisha | Wing structure and profile |
WO2013079918A1 (en) * | 2011-12-01 | 2013-06-06 | Airbus Operations Limited | Leading edge structure |
-
1946
- 1946-08-01 GB GB22904/46A patent/GB615284A/en not_active Expired
Cited By (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP1371551A1 (en) * | 2002-06-12 | 2003-12-17 | Honda Giken Kogyo Kabushiki Kaisha | Wing structure and profile |
US6834830B2 (en) | 2002-06-12 | 2004-12-28 | Honda Giken Kogyo Kabushiki Kaisha | Main wing structure |
WO2013079918A1 (en) * | 2011-12-01 | 2013-06-06 | Airbus Operations Limited | Leading edge structure |
CN103958345A (en) * | 2011-12-01 | 2014-07-30 | 空中客车营运有限公司 | Leading edge structure |
JP2015502883A (en) * | 2011-12-01 | 2015-01-29 | エアバス オペレーションズ リミテッドAirbus Operations Limited | Leading edge structure |
CN103958345B (en) * | 2011-12-01 | 2017-03-15 | 空中客车营运有限公司 | Leading edge structure |
US11247766B2 (en) | 2011-12-01 | 2022-02-15 | Airbus Operations Limited | Leading edge structure |
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