US2292372A - Structural element - Google Patents

Structural element Download PDF

Info

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
Application number
US404380A
Inventor
Glendon T Gerlach
Altman Peter
Alfred S Kos
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
VULTEE AIRCRAFT Inc
Original Assignee
VULTEE AIRCRAFT Inc
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by VULTEE AIRCRAFT Inc filed Critical VULTEE AIRCRAFT Inc
Priority to US404380A priority Critical patent/US2292372A/en
Application granted granted Critical
Publication of US2292372A publication Critical patent/US2292372A/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

Links

Images

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12Construction or attachment of skin panels
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06Frames; Stringers; Longerons ; Fuselage sections
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C1/00Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C2001/0054Fuselage structures substantially made from particular materials
    • B64C2001/0081Fuselage 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.
US404380A 1941-07-28 1941-07-28 Structural element Expired - Lifetime US2292372A (en)

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
US (1) US2292372A (en)

Cited By (15)

* Cited by examiner, † Cited by third party
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

Cited By (36)

* Cited by examiner, † Cited by third party
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

Similar Documents

Publication Publication Date Title
US2292372A (en) Structural element
US2749061A (en) Airplane wing stress compensating structure assembly
US2654686A (en) Stiffened honeycomb core
US2389767A (en) Structural frame
US2887762A (en) Method of making prestressed structural member
US2431184A (en) Composite blade
US3217807A (en) Rotor blade
US3002567A (en) Spar for sustaining rotors
US3140081A (en) Tube form mounting
US2807435A (en) Turbine stator blade
US1924880A (en) Open truss girder
US2941603A (en) Helicopter rotor blade
US3034608A (en) Sheet stiffening stringer
US2364494A (en) Method of applying covering to airplane wing frames
US2434232A (en) Grille
US1643577A (en) Hollow light-metal girder
GB524721A (en) Improvements in and relating to "stressed skin" fuselages or nacelles for aircraft
US2324229A (en) Lattice structure
US2382835A (en) Load-carrying member
US2311683A (en) Airplane wing construction
US1791827A (en) Truss structure
US2384409A (en) Airfoil structure for aircraft
US1717390A (en) Aircraft
GB559954A (en) Airplane structures
US2194483A (en) Airplane rib