US2292372A - Structural element - Google Patents
Structural element Download PDFInfo
- Publication number
- US2292372A US2292372A US404380A US40438041A US2292372A US 2292372 A US2292372 A US 2292372A US 404380 A US404380 A US 404380A US 40438041 A US40438041 A US 40438041A US 2292372 A US2292372 A US 2292372A
- Authority
- US
- United States
- Prior art keywords
- sheet
- rows
- bonds
- expanded metal
- portions
- 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 - Lifetime
Links
- 229910052751 metal Inorganic materials 0.000 description 26
- 239000002184 metal Substances 0.000 description 25
- 229910052782 aluminium Inorganic materials 0.000 description 3
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 description 3
- 229910000831 Steel Inorganic materials 0.000 description 1
- 244000309464 bull Species 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000002787 reinforcement Effects 0.000 description 1
- 239000010959 steel Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
- B64C1/12—Construction or attachment of skin panels
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
- B64C2001/0054—Fuselage structures substantially made from particular materials
- B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials
Definitions
- the invention relates to metal elements such as bulkheads.
- One object of the invention is to provide a bull:- head which comprises expandedmetal and a thin skin-forming sheet, the expanded metal having arched deformed portions and strips spaced from the sheet and connecting the arched portions so the bulkhead will have a high strength-weight ratio and transverse rigidity and which can be substituted for elements of light weight metal, such as aluminum.
- the invention consists in the several novel fea tures which are hereinafter set forth and are more particularly defined by claims at theconclusion hereof.
- Fig. 1 is a face view of a bulkhead embodying the invention.
- Fig. 2 is a section on line 22 of Fig. 1.
- Fig. 3 is a face view of a portion of the bulkhead on a somewhat larger scale.
- Fig. 4 is a section taken on line 1-6 of Fig. 3.
- Fig. 5 is a view of a modified form of the invention.
- the invention is exemplified in a bulkhead of oval contour which maybe used in airplane structures.
- the bulkhead comprises a rim l0, angular in cross-section and bent to the desired contour of the margin of the bulkhead.
- a sheet H of thin skin-forming metal, such as steel, has its margin spot-welded to one of the flanges of the rim l0.
- Diamond-mesh expanded metal I! is spot-welded at spaced points throughout the entire area of the sheet H.
- the expanded metal is of the diamond-mesh type which has been flattened so that the faces of the bonds and strands will be coplaner and comprises diagonal strands ll joined by bonds l3.
- the strands of the flattened expanded metal are bent, before said metal is spot-welded to sheet ii, to form a succession of rows of arched or substantially V- shaped portions 15.
- the faces N of the intermediate rows of bonds R3 are coplaner and spaced transversely away from the sheet. lhe rows of arched portions extend entirely across the sheet.
- the faces Hi or" alternate rows of bonds i3 are spot-welded to the sheet, as at Iii.
- channelled strips comprise a web H which fits the faces I3 of the bonds and inclined divergent flanges is which fit against the outer portions of the strands in alternating rows of arched portions I5. These strips are spotwelded to the bonds of the expanded metal as at 29.
- a bulkhead composed of a sheet .007" in thickness and diamond-mesh expanded metal with a long axis of 3.25 and a short axis 1.56" (before the arched portions are formed therein) and the strands approximately .050" in thickness, without regard to the reinforcement formed by the arched portions of the expanded metal and the ridge-strips, has greater transverse strength under compression than aluminum .032" in thickness and that the weight of the bulkhead will be no greater than when formed of aluminum.
- the arched portions of the expanded metal and the strips provide adequate transverse strength for predetermined loads;
- the strips may extend across transverse rows of the arched portions of the expanded metal. as illustrated in Fig. 3, or may extend across longitudinal rows of the arched portions, as illustrated in Fig. 5.
- the invention exemplifies a structural element. such as a bulkhead, having a high strengthweight ratio and in which a thin skin-forming sheet is adequately reinforced to resist transvers stresses or deflections.
- a structural element comprising a thin skinforming sheet, expanded metal having a substantially continuous succession of rows of arched portions between alternate rows of the bonds oi the expanded metal extending transversely away from the sheet, the portions between the arched portions being bonded to the sheet, and strips extending across and bonded to the rows of the arched portions of the expanded metal and spaced transversely from the sheet.
- a structural element comprising a thin skinforining sheet, flattened expanded metal having a substantially continuous succession ofrows of arched portions between alternate rows of the bonds of the expanded metal extending transversely away from the sheet, the portions between the arched portions being bonded to one face of the sheet, strips extending across and bonded to the rows of the arched portions of the expanded metal and spaced transversely from the sheet, and a rim secured to the other face of the sheet.
- a structural element comprising a thin skinforming sheet, flattened expanded metal having a substantially continuous succession of rows of arched portions between alternate rows of the bonds of the expanded metal extending transversely away from the sheet, the portions between the arched portions being bonded to the sheet, and strips extending across and bonded to the rows of the arched portions of the expanded metal and spaced transversely from the sheet, said strips having divergent flanges extending toward the sheet.
- a structural element comprising a thin skinforming sheet of metal and diamond-mesh expanded metal having a substantially continuous succession of rows of arched portions with the bonds in alternate rows coplaner and bonded to the sheet and the bonds at intermediate rows coplaner and spaced apart transversely from the sheet, and strips extending along and welded to the bonds in the intermediate rows.
- a structural element comprising a thin skin- Iorming sheet of metal and diamond-mesh expanded metal having a substantially continuous succession of rows of arched portions with the bonds in alternate rows coplaner and bonded to the sheet and the bonds 0! intermediate rows coplaner and spaced apart transversely from the sheet, and strips extending along the welded to the bonds in the intermediate rows, the strips having flanges extending toward the sheet.
Description
11, 1942- I G. T. GERLACH ET L 2,292,372
STRUCTURAL ELEMENT Filed July 28, 1941 Patented Aug. 11, 1942 STRUCTURAL ELEMENT Glendon '1. Gerlach, Peter Altman, and Alfred S.
Kos, Detroit, Mich, assignors to Vultee Aircraft, Ina, Vultee Field, CaliL, a corporation of? Delaware Application July 28, 1941, Serial No. 404,380
Claims.
The invention relates to metal elements such as bulkheads.
One object of the invention is to provide a bull:- head which comprises expandedmetal and a thin skin-forming sheet, the expanded metal having arched deformed portions and strips spaced from the sheet and connecting the arched portions so the bulkhead will have a high strength-weight ratio and transverse rigidity and which can be substituted for elements of light weight metal, such as aluminum.
Other objects of the invention will appear from the detailed description.
The invention consists in the several novel fea tures which are hereinafter set forth and are more particularly defined by claims at theconclusion hereof.
In the drawingzFig. 1 is a face view of a bulkhead embodying the invention. Fig. 2 is a section on line 22 of Fig. 1. Fig. 3 is a face view of a portion of the bulkhead on a somewhat larger scale. Fig. 4 is a section taken on line 1-6 of Fig. 3. Fig. 5 is a view of a modified form of the invention.
The invention is exemplified in a bulkhead of oval contour which maybe used in airplane structures. The bulkhead comprises a rim l0, angular in cross-section and bent to the desired contour of the margin of the bulkhead. A sheet H of thin skin-forming metal, such as steel, has its margin spot-welded to one of the flanges of the rim l0. Diamond-mesh expanded metal I! is spot-welded at spaced points throughout the entire area of the sheet H. The expanded metal is of the diamond-mesh type which has been flattened so that the faces of the bonds and strands will be coplaner and comprises diagonal strands ll joined by bonds l3. The strands of the flattened expanded metal are bent, before said metal is spot-welded to sheet ii, to form a succession of rows of arched or substantially V- shaped portions 15. This results in, coplaner faces iii in the alternating rows of bonds which fit against oneface of the sheet H. The faces N of the intermediate rows of bonds R3 are coplaner and spaced transversely away from the sheet. lhe rows of arched portions extend entirely across the sheet. The faces Hi or" alternate rows of bonds i3 are spot-welded to the sheet, as at Iii. channelled strips comprise a web H which fits the faces I3 of the bonds and inclined divergent flanges is which fit against the outer portions of the strands in alternating rows of arched portions I5. These strips are spotwelded to the bonds of the expanded metal as at 29.
In fabricating the bulkhead the strips H are welded to the faces 63 of the bonds before the faces 83 are welded to the sheet "I.
In practice, it has been found that a bulkhead composed of a sheet .007" in thickness and diamond-mesh expanded metal with a long axis of 3.25 and a short axis 1.56" (before the arched portions are formed therein) and the strands approximately .050" in thickness, without regard to the reinforcement formed by the arched portions of the expanded metal and the ridge-strips, has greater transverse strength under compression than aluminum .032" in thickness and that the weight of the bulkhead will be no greater than when formed of aluminum. The arched portions of the expanded metal and the strips provide adequate transverse strength for predetermined loads;
The strips may extend across transverse rows of the arched portions of the expanded metal. as illustrated in Fig. 3, or may extend across longitudinal rows of the arched portions, as illustrated in Fig. 5.
The invention exemplifies a structural element. such as a bulkhead, having a high strengthweight ratio and in which a thin skin-forming sheet is adequately reinforced to resist transvers stresses or deflections.
The invention is not to be understood as restricted to the details set forth, since these may be modified within the scope of the appended claims, without departing from the spirit and scope of the invention.
'.Having thus described the invention, what we claim as new and desire to secure by Letters Patent is:
1. A structural element comprising a thin skinforming sheet, expanded metal having a substantially continuous succession of rows of arched portions between alternate rows of the bonds oi the expanded metal extending transversely away from the sheet, the portions between the arched portions being bonded to the sheet, and strips extending across and bonded to the rows of the arched portions of the expanded metal and spaced transversely from the sheet.
2. A structural element comprising a thin skinforining sheet, flattened expanded metal having a substantially continuous succession ofrows of arched portions between alternate rows of the bonds of the expanded metal extending transversely away from the sheet, the portions between the arched portions being bonded to one face of the sheet, strips extending across and bonded to the rows of the arched portions of the expanded metal and spaced transversely from the sheet, and a rim secured to the other face of the sheet.
3. A structural element comprising a thin skinforming sheet, flattened expanded metal having a substantially continuous succession of rows of arched portions between alternate rows of the bonds of the expanded metal extending transversely away from the sheet, the portions between the arched portions being bonded to the sheet, and strips extending across and bonded to the rows of the arched portions of the expanded metal and spaced transversely from the sheet, said strips having divergent flanges extending toward the sheet.
4. A structural element comprising a thin skinforming sheet of metal and diamond-mesh expanded metal having a substantially continuous succession of rows of arched portions with the bonds in alternate rows coplaner and bonded to the sheet and the bonds at intermediate rows coplaner and spaced apart transversely from the sheet, and strips extending along and welded to the bonds in the intermediate rows.
5. A structural element comprising a thin skin- Iorming sheet of metal and diamond-mesh expanded metal having a substantially continuous succession of rows of arched portions with the bonds in alternate rows coplaner and bonded to the sheet and the bonds 0! intermediate rows coplaner and spaced apart transversely from the sheet, and strips extending along the welded to the bonds in the intermediate rows, the strips having flanges extending toward the sheet.
GLENDON T. GERLACH. PETER ALTNIAN. ALFRED S. KOS.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US404380A US2292372A (en) | 1941-07-28 | 1941-07-28 | Structural element |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US404380A US2292372A (en) | 1941-07-28 | 1941-07-28 | Structural element |
Publications (1)
Publication Number | Publication Date |
---|---|
US2292372A true US2292372A (en) | 1942-08-11 |
Family
ID=23599369
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US404380A Expired - Lifetime US2292372A (en) | 1941-07-28 | 1941-07-28 | Structural element |
Country Status (1)
Country | Link |
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US (1) | US2292372A (en) |
Cited By (15)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2434232A (en) * | 1945-06-29 | 1948-01-06 | Bendix Aviat Corp | Grille |
US2441476A (en) * | 1944-08-10 | 1948-05-11 | Glenn L Martin Co | Reinforced structural sheet |
US2771164A (en) * | 1949-01-27 | 1956-11-20 | Western Engineering Associates | Wall construction |
US3274739A (en) * | 1962-06-07 | 1966-09-27 | Gregoire Engineering And Dev C | Sheet panel assembly and supporting members therefor |
US3702046A (en) * | 1970-10-12 | 1972-11-07 | Braden Steel Corp | Prefabricated building sections |
US4241146A (en) * | 1978-11-20 | 1980-12-23 | Eugene W. Sivachenko | Corrugated plate having variable material thickness and method for making same |
US4396685A (en) * | 1980-11-13 | 1983-08-02 | Ampliform Pty. Limited | Fabricated expanded metal |
US20050263645A1 (en) * | 2004-04-06 | 2005-12-01 | Kent Johnson | Structural panels for use in aircraft fuselages and other structures |
US20060060705A1 (en) * | 2004-09-23 | 2006-03-23 | Stulc Jeffrey F | Splice joints for composite aircraft fuselages and other structures |
US20060108058A1 (en) * | 2004-11-24 | 2006-05-25 | Chapman Michael R | Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections |
US20060226287A1 (en) * | 2004-04-06 | 2006-10-12 | Kent Grantham | Structural panels for use in aircraft fuselages and other structures |
US20080230652A1 (en) * | 2004-04-06 | 2008-09-25 | Biornstad Robert D | Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections |
US8042767B2 (en) | 2007-09-04 | 2011-10-25 | The Boeing Company | Composite fabric with rigid member structure |
US8388795B2 (en) | 2007-05-17 | 2013-03-05 | The Boeing Company | Nanotube-enhanced interlayers for composite structures |
US11560211B2 (en) * | 2018-12-20 | 2023-01-24 | Premium Aerotec Gmbh | Fuselage component for an aircraft, method for producing a fuselage component, and aircraft |
-
1941
- 1941-07-28 US US404380A patent/US2292372A/en not_active Expired - Lifetime
Cited By (36)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2441476A (en) * | 1944-08-10 | 1948-05-11 | Glenn L Martin Co | Reinforced structural sheet |
US2434232A (en) * | 1945-06-29 | 1948-01-06 | Bendix Aviat Corp | Grille |
US2771164A (en) * | 1949-01-27 | 1956-11-20 | Western Engineering Associates | Wall construction |
US3274739A (en) * | 1962-06-07 | 1966-09-27 | Gregoire Engineering And Dev C | Sheet panel assembly and supporting members therefor |
US3702046A (en) * | 1970-10-12 | 1972-11-07 | Braden Steel Corp | Prefabricated building sections |
US4241146A (en) * | 1978-11-20 | 1980-12-23 | Eugene W. Sivachenko | Corrugated plate having variable material thickness and method for making same |
US4396685A (en) * | 1980-11-13 | 1983-08-02 | Ampliform Pty. Limited | Fabricated expanded metal |
US7159822B2 (en) * | 2004-04-06 | 2007-01-09 | The Boeing Company | Structural panels for use in aircraft fuselages and other structures |
US20100083504A1 (en) * | 2004-04-06 | 2010-04-08 | The Boeing Company | Methods of manufacturing structural panels |
US20050263645A1 (en) * | 2004-04-06 | 2005-12-01 | Kent Johnson | Structural panels for use in aircraft fuselages and other structures |
US20060226287A1 (en) * | 2004-04-06 | 2006-10-12 | Kent Grantham | 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 |
US8496206B2 (en) | 2004-04-06 | 2013-07-30 | The Boeing Company | Structural panels for use in aircraft fuselages and other structures |
US8382037B2 (en) | 2004-04-06 | 2013-02-26 | The Boeing Company | Composite barrel sections for aircraft fuselages and other structures |
US20080230652A1 (en) * | 2004-04-06 | 2008-09-25 | Biornstad Robert D | Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections |
US8182628B2 (en) | 2004-04-06 | 2012-05-22 | The Boeing Company | Composite barrel sections for aircraft fuselages and other structures, and methods for systems for manufacturing such barrel sections |
US8157212B2 (en) | 2004-04-06 | 2012-04-17 | The Boeing Company | Composite barrel sections for aircraft fuselages and other structures, and methods and systems for manufacturing such barrel sections |
US7716835B2 (en) | 2004-04-06 | 2010-05-18 | The Boeing Company | Methods of manufacturing structural panels |
US20100223772A1 (en) * | 2004-04-06 | 2010-09-09 | The Boeing Company | Structural Panels for Use in Aircraft Fuselages and Other Structures |
US9738371B2 (en) | 2004-09-23 | 2017-08-22 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
US8061035B2 (en) | 2004-09-23 | 2011-11-22 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
US20060060705A1 (en) * | 2004-09-23 | 2006-03-23 | Stulc Jeffrey F | Splice joints for composite aircraft fuselages and other structures |
US8882040B2 (en) | 2004-09-23 | 2014-11-11 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
US10689086B2 (en) | 2004-09-23 | 2020-06-23 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
US8869403B2 (en) | 2004-09-23 | 2014-10-28 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
US7325771B2 (en) | 2004-09-23 | 2008-02-05 | The Boeing Company | Splice joints for composite aircraft fuselages and other structures |
US20060108058A1 (en) * | 2004-11-24 | 2006-05-25 | Chapman Michael R | Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections |
US8418740B2 (en) | 2004-11-24 | 2013-04-16 | The Boeing Company | Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections |
US8303758B2 (en) | 2004-11-24 | 2012-11-06 | The Boeing Company | Methods for manufacturing composite sections for aircraft fuselages and other structures |
US8168023B2 (en) | 2004-11-24 | 2012-05-01 | The Boeing Company | Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections |
US7503368B2 (en) | 2004-11-24 | 2009-03-17 | The Boeing Company | Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections |
US8388795B2 (en) | 2007-05-17 | 2013-03-05 | The Boeing Company | Nanotube-enhanced interlayers for composite structures |
US8657990B2 (en) | 2007-05-17 | 2014-02-25 | The Boeing Company | Nanotube-enhanced interlayers for composite structures |
US8728263B2 (en) | 2007-09-04 | 2014-05-20 | The Boeing Company | Composite fabric with rigid member structure |
US8042767B2 (en) | 2007-09-04 | 2011-10-25 | The Boeing Company | Composite fabric with rigid member structure |
US11560211B2 (en) * | 2018-12-20 | 2023-01-24 | Premium Aerotec Gmbh | Fuselage component for an aircraft, method for producing a fuselage component, and aircraft |
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