GB194516A - Improvements in or connected with the construction of wings and like parts of aeroplane flying machines and other aircraft - Google Patents
Improvements in or connected with the construction of wings and like parts of aeroplane flying machines and other aircraftInfo
- Publication number
- GB194516A GB194516A GB4567/22A GB456722A GB194516A GB 194516 A GB194516 A GB 194516A GB 4567/22 A GB4567/22 A GB 4567/22A GB 456722 A GB456722 A GB 456722A GB 194516 A GB194516 A GB 194516A
- Authority
- GB
- United Kingdom
- Prior art keywords
- rib
- edges
- flanges
- spars
- ribs
- 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
194,516. Short, H. O. Feb. 16, 1922. Framework; planes and the like, construction of.-For facilitating the removal of damaged ribs of planes without interfering with undamaged ones, the ribs are made singly detachable by constructing them in two or more sections. In the construction shown in Fig. 1, a metal rib is formed of two approximately equal sections 1, 2, provided with flanged semicircular recesses 8 which embrace the spars 3 : (the front spar only is shown in the figures). The contacting portions 5 of the edges of the two sections, adjacent the recesses 8, are flanged and riveted together, whilst the edges 6 at the rear and forward ends of the rib, are overlapped and riveted as shown, or abut and are held together by a riveted cover plate. The flanges embracing the spars may be drawn together by a clamping ring 9, Fig. 4, tightened by a bolt 10, the connecting flanges 5 being suitably recessed adjacent the flanges 8. Flanged apertures 11, Fig. 1, may be formed in the rib for decreasing its weight. According to another construction, the main portion of the rib 12, Fig. 5, is made in one piece but where a spar 3 is to pass, a slot having a semicircular base is cut. When the rib is fitted the spars pass through the slots until they become seated on the bases of the slots, and cover plates 13 having lower edges conforming with the seetion of the spars are then fixed to the rib by riveting together flanges 14, 15 on the perpendicular edges of the slots and the cover plates. Both the rib and the cover plates are flanged where they embrace the spars. In a modification the cover plate overlaps the rib and is rivetted to it. Fig. 7 illustrates the manner in which an outer metal covering is applied to a wing using the ribs described, two ribs 17 and a portion of a spar 3 being shown. The covering consists of strips 18 of sheet metal extending in the direction of flight, each strip having flanges at its side edges abutting against the edges of the ribs 17. Channel strips 19 are passed over the flanges and rib edges, and the whole riveted together.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB4567/22A GB194516A (en) | 1922-02-16 | 1922-02-16 | Improvements in or connected with the construction of wings and like parts of aeroplane flying machines and other aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB4567/22A GB194516A (en) | 1922-02-16 | 1922-02-16 | Improvements in or connected with the construction of wings and like parts of aeroplane flying machines and other aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB194516A true GB194516A (en) | 1923-03-15 |
Family
ID=9779575
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB4567/22A Expired GB194516A (en) | 1922-02-16 | 1922-02-16 | Improvements in or connected with the construction of wings and like parts of aeroplane flying machines and other aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB194516A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008012569A3 (en) * | 2006-07-28 | 2009-03-12 | Airbus Uk Ltd | Aircrat wing box and manufacture thereof |
| EP3718878A1 (en) * | 2019-04-02 | 2020-10-07 | The Boeing Company | Mechanical fastening system and associated structural assembly and method |
| US10814956B2 (en) | 2016-05-05 | 2020-10-27 | The Boeing Company | Mechanical fastening system and associated structural assembly and method |
-
1922
- 1922-02-16 GB GB4567/22A patent/GB194516A/en not_active Expired
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2008012569A3 (en) * | 2006-07-28 | 2009-03-12 | Airbus Uk Ltd | Aircrat wing box and manufacture thereof |
| US8172179B2 (en) | 2006-07-28 | 2012-05-08 | Airbus Operations Limited | Aircraft wing box and manufacture thereof |
| US10814956B2 (en) | 2016-05-05 | 2020-10-27 | The Boeing Company | Mechanical fastening system and associated structural assembly and method |
| EP3718878A1 (en) * | 2019-04-02 | 2020-10-07 | The Boeing Company | Mechanical fastening system and associated structural assembly and method |
| CN111792019A (en) * | 2019-04-02 | 2020-10-20 | 波音公司 | Mechanical fastening system and related structural assembly and method |
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