GB303360A - Improvements in metal aircraft wings - Google Patents
Improvements in metal aircraft wingsInfo
- Publication number
- GB303360A GB303360A GB37690/28A GB3769028A GB303360A GB 303360 A GB303360 A GB 303360A GB 37690/28 A GB37690/28 A GB 37690/28A GB 3769028 A GB3769028 A GB 3769028A GB 303360 A GB303360 A GB 303360A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wing
- webs
- girder
- spars
- box
- 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
Abstract
303,360. Rohrbach Metall-Flugzeugbau Ges. Dec. 31, 1927, [Convention date]. Addition to 274,085. Planes, construction of.-The central box-girder portion of a hollow metal aircraft wing has the webs of its longitudinal and transverse walls and the skin constructed with thin metal webs which develop oblique folds under stress as described in the parent Specification. Fig. 2 shows a wing in which the central portion forms a box-girder of which the webs x, 5, of the spars and ribs and also the upper and lower coverings are formed of thin metal developing oblique folds under stress. The webs are strengthened by channel members y, 7 secured to the webs and booms and the skin is supported by similar members. Holes 1, 8, 11 give access to the interior of the wing, the edges of the holes being reinforced and watertight covers being provided. These may be used also on the wings described in the parent Specification. Watertight hollow fairing pieces w are secured to the box-girder by hinges. The booms of the spars have several layers of metal of different thickness, the outer layers being the thickest. A wing with a single spar also is described, the front portion of the wing being formed as a torsion resisting girder. A wing with three spars also is described.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| DE303360X | 1927-12-31 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB303360A true GB303360A (en) | 1929-11-07 |
Family
ID=6111288
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB37690/28A Expired GB303360A (en) | 1927-12-31 | 1928-12-20 | Improvements in metal aircraft wings |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB303360A (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2451458A (en) * | 1943-06-28 | 1948-10-12 | Budd Co | Aircraft airfoil construction |
| US2451454A (en) * | 1943-06-28 | 1948-10-12 | Budd Co | Method of fabricating airfoils |
| US2469480A (en) * | 1943-10-13 | 1949-05-10 | United Aircraft Corp | Rotor blade |
| US2606728A (en) * | 1945-12-04 | 1952-08-12 | United Aircraft Corp | Rotor blade |
| US6237873B1 (en) * | 1998-06-23 | 2001-05-29 | Fuji Jukogyo Kabushiki Kaisha | Composite material wing structure |
-
1928
- 1928-12-20 GB GB37690/28A patent/GB303360A/en not_active Expired
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2451458A (en) * | 1943-06-28 | 1948-10-12 | Budd Co | Aircraft airfoil construction |
| US2451454A (en) * | 1943-06-28 | 1948-10-12 | Budd Co | Method of fabricating airfoils |
| US2469480A (en) * | 1943-10-13 | 1949-05-10 | United Aircraft Corp | Rotor blade |
| US2606728A (en) * | 1945-12-04 | 1952-08-12 | United Aircraft Corp | Rotor blade |
| US6237873B1 (en) * | 1998-06-23 | 2001-05-29 | Fuji Jukogyo Kabushiki Kaisha | Composite material wing structure |
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