GB589161A - Improvements in means for attaching metal skins of aircraft components to their supporting structures - Google Patents
Improvements in means for attaching metal skins of aircraft components to their supporting structuresInfo
- Publication number
- GB589161A GB589161A GB6600/45A GB660045A GB589161A GB 589161 A GB589161 A GB 589161A GB 6600/45 A GB6600/45 A GB 6600/45A GB 660045 A GB660045 A GB 660045A GB 589161 A GB589161 A GB 589161A
- Authority
- GB
- United Kingdom
- Prior art keywords
- skin
- jig
- edges
- sheets
- securing
- 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
- 239000002184 metal Substances 0.000 title 1
- 238000010438 heat treatment Methods 0.000 abstract 3
- 238000005553 drilling Methods 0.000 abstract 1
- 230000001939 inductive effect Effects 0.000 abstract 1
- 238000003780 insertion Methods 0.000 abstract 1
- 230000037431 insertion Effects 0.000 abstract 1
- 239000007788 liquid Substances 0.000 abstract 1
- 238000000034 method Methods 0.000 abstract 1
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
- B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
- B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
- B64F5/10—Manufacturing or assembling aircraft, e.g. jigs therefor
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Mechanical Engineering (AREA)
- Transportation (AREA)
- Lining Or Joining Of Plastics Or The Like (AREA)
Abstract
589,161. Aircraft structures. HAWKER AIRCRAFT, Ltd., BETTERIDGE, P. D., and ROWE, E. T. March 15, 1945, No. 6600. [Class 4] In order to impart a smooth surface, free from irregularities, to the skin of aircraft components, a predetermined tension is imparted to the skin prior to its application to the supporting structure and maintained during the application of the skin. The skin may be stressed by springs, or by heating same, securing its edges to a rigid frame while expanded and then allowing it to cool. Heating may be effected by electric pads, steam, or heated liquid. In the case of components such as ailerons, elevators, or flaps, which are of narrow chord in proportion to their length stress may be applied in the direction of their length only. Fig. 1 shows a jig for the assembly of such a long, narrow, component comprising rib-locating members 18 at the base and spring tensioners 22 passing through side members 12 and connected to rigid clamps 24, secured to the narrow ends of the plate 20. The tensioning members are capable of adjustment to enable the stress applied to the skin to be varied. For stressing larger sheets, holes may be drilled along its edges for the insertion of the ends of springs carried by a jig frame extending around the edges of the sheet (Fig. 7, not shown). Figs. 3 and 6 show an arrangement suitable for the assembly of a fin or rudder, the base 42 of the jig having an opening 44, conforming to the spar contour, and a vertical plate 46 having an opening 48, conforming to the profile of the component. The sides of the jig are formed by inclinedmembers 52. The component is assembled by inserting the ribs 59 and associated structure, laying the skin sheets 66 on opposite sides of the jig, heating the sheets, for example, by electric pads 62, drilling holes at the edges of.the sheets corresponding to holes 56 along the edges of the jig for the reception of securing bolts, allowing the .sheets to cool to induce the desired stress, and then securing them in position by rivets passing through the sheets and internal structural members. An alternative method of inducing stress .in the skin consists in securing its edges to a rigid frame, the latter of which is heated and thereby expanded, (Fig. 8, not shown).
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB6600/45A GB589161A (en) | 1945-03-15 | 1945-03-15 | Improvements in means for attaching metal skins of aircraft components to their supporting structures |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB6600/45A GB589161A (en) | 1945-03-15 | 1945-03-15 | Improvements in means for attaching metal skins of aircraft components to their supporting structures |
Publications (1)
Publication Number | Publication Date |
---|---|
GB589161A true GB589161A (en) | 1947-06-12 |
Family
ID=9817442
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB6600/45A Expired GB589161A (en) | 1945-03-15 | 1945-03-15 | Improvements in means for attaching metal skins of aircraft components to their supporting structures |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB589161A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1001125B (en) * | 1953-05-11 | 1957-01-17 | Daimler Benz Ag | Process for the production of structural parts which consist of sheet metal and stiffening members connected to it |
US3082519A (en) * | 1957-12-16 | 1963-03-26 | United States Steel Corp | Method for making metal panels |
CN113844672A (en) * | 2020-06-28 | 2021-12-28 | 航天特种材料及工艺技术研究所 | Assembly fixture and assembly method for composite material unmanned aerial vehicle vertical fin |
CN114476117A (en) * | 2022-02-23 | 2022-05-13 | 南京航空航天大学 | Box section type fuselage assembly process based on force position coupling |
-
1945
- 1945-03-15 GB GB6600/45A patent/GB589161A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
DE1001125B (en) * | 1953-05-11 | 1957-01-17 | Daimler Benz Ag | Process for the production of structural parts which consist of sheet metal and stiffening members connected to it |
US3082519A (en) * | 1957-12-16 | 1963-03-26 | United States Steel Corp | Method for making metal panels |
CN113844672A (en) * | 2020-06-28 | 2021-12-28 | 航天特种材料及工艺技术研究所 | Assembly fixture and assembly method for composite material unmanned aerial vehicle vertical fin |
CN113844672B (en) * | 2020-06-28 | 2023-04-11 | 航天特种材料及工艺技术研究所 | Assembly fixture and assembly method for composite material unmanned aerial vehicle vertical fin |
CN114476117A (en) * | 2022-02-23 | 2022-05-13 | 南京航空航天大学 | Box section type fuselage assembly process based on force position coupling |
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