US2325900A - Airplane construction - Google Patents

Airplane construction Download PDF

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Publication number
US2325900A
US2325900A US425476A US42547642A US2325900A US 2325900 A US2325900 A US 2325900A US 425476 A US425476 A US 425476A US 42547642 A US42547642 A US 42547642A US 2325900 A US2325900 A US 2325900A
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Prior art keywords
tubes
web
airplane
openings
edge
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Expired - Lifetime
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US425476A
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Joseph K Anderson
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Individual
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Individual
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Priority to US425476A priority Critical patent/US2325900A/en
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Publication of US2325900A publication Critical patent/US2325900A/en
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers
    • 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
    • B64C1/061—Frames
    • 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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the presentainvention relates to new and use ful improvementsin theconstruction of airplane wings, fuselages, and other parts of an airplane, and has forits.
  • primary object to provide a frame construction for carrying the fabric or covering of the wings, fuselage, and other parts of the airplane.
  • a further object is to provide a frame construction which is strong and durable, relatively inexpensive to manufacture, in which the weight of V V the frame is materially reduced and which at the same time isotherwise well adapted for the purposes for which the same is intended.
  • Figure 1 is a fragmentary perspective view of a portion of the frame showing the tube for receiving the fabric covering secured to one of the of a frame member
  • Figure 7 is a transversesectional view thereof.
  • Figure 8 is a transverse sectional view illustrating the use of the frame construction for a tubular part of an airplane body, such as the fuselage.
  • Figure 9 is a side elevational view of a modified form of frame construction, with parts broken away.
  • ber generally which is composed of a pair of metal.
  • Figure 10 is a fragmentary edge elevational tubes G S,- each-of the tubes being split-longitudinally as shown at 1-1 for receiving-the edge portion-of ametal web memberfl, the edges of the web being inserted through the slots 'lofthe respective-tubes. and" welded to the interior of the tubes at a surface thereof diametrically opposite from the slot '1. Openings 9 are formed in the web 8 to reduce the weight thereof.
  • plurality of fabricretaining tubes ID are welded, as at l l to the top and bottom of the tubes 6, the tubes H3 extending at right angles to the tubes 6 and transversely of the wings.
  • the tubes In at the top and bottom of the wing are preferably connected at the leading trailing edges of the wing.
  • A. handle is may be detachably secured to the strand 7 [4 adjacent its inserted end for guiding the strand through the tubes, the handle 16 being movable along the slots I2.
  • the longitudinal frame membersof the Wing are designated at H and are constructed of the tubes 6 and web B and the fabric-covering receiving tubes 18 extend transversely thereof and are provided with the longitudinal slots l9' therein for receiving the fabric covering as heretofore explained.
  • the frame is designated generally at .26 composed of' the ring-like tubular member 2
  • a plurality of openings 23 are formed in the Web adjacent the outer edge thereof, the openings being interrupted to provide communication through said edge. Positioned in the openings are longitudinally extending tubes 24 corresponding to the tubes In and having slots therein registering with the interrupted edge of the openings 23 for receiving the fabric 25 secured" in the tubes by its flexible strand 26.
  • Figures 9 to 12,.inclusive, represent a modified form of flat frame construction in which the web other edge of the web is inserted into the continuous slot 30 of the tube 3
  • at its side opposite from the slot '30 is formed with longitudinally spaced slots 32 through which project extensions 33 on the inner end of the web.
  • the extensions are also provided with the openings 34 adapted for receiving the fabric-retaining tubes 35 at the opposite edge of the frame.
  • the tubes 29 and 35 are secured in the openings of the web by welding or in any other suitable manner.
  • FIG. 13 a curved frame: construction is illustrated embodying the web 36, extension 31, frame tube 38, and fabric-retaining tubes 39 and a 40 at the opposite edges of the web and assem- Having thus described the invention what ll claim is:
  • a frame construction for an airplane com- I receiving the fabric retaining tubes 29 and the prising a ring-like tube having a circumferential slot in its outer periphery, a ring-like web having itsinner edge inserted in said slot and abutting the inner wall of the tube at a point diametrically opposite to the slot, said web having openings adjacent its peripheral edge and having a narrow entrance slot communicating with each opening, and axially extending fabric retaining tubes positioned in said openings and having fabric receiving slots in registry with the entrance slotsof the openings.
  • a frame construction for airplanes comprising a web member having openings adjacent one edge, a tube having a longitudinal slot therein receiving the other edge of the web, said tube also having spaced slots in it side opposite from the first-named slot, extensions on said other edge of the web one of said extensions projecting through .each of the last-named slots outwardly of thetube, said extension also having openings therein, and fabric-retaining tubes positioned in said openings for extending at right angles to the web.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Toys (AREA)

Description

Aug-3,1943 J.'K. ANDERSON 2,325,900
AIRPLANE CONSTRUCTION Filed Jan. 2, 1942 4 Sheets-Sheet 1 Inventor I L/QSEPH K. fl/vaf/aso w By @k z Z ll Iloruq 1' Aug. 3, 1943.
J. K. ANDERSON AIRPLANE CONSTRUCTION Filed Jan. 2, 1942 4 Sheets-Sheet 2 Aug. 3, 1943.
J. K. ANDERSON 2,325,900
AIRPLANE CONSTRUCTION Filed Jan. 2, 1942 Sheets-Sheet. 5
Im'entor JOSEPH K. ANDERSON,
A Home Aug. 3, 1943.
' J. ANDERSON AIRPLANE CONSTRUCTION Filed Jan. 2, 1942 4 Sheets-Sheet 4 Joan/1 K Z/Ammw/v,
Attorney for an airplane wing.
Patented Aug. 3, 1943 I AmP AnEcoNsrRUoTIoN r 7 Joseph K; Anderson, rammin Ohio" 7 f ApplicationJanuary 2, 1942, Serial No. 425,476 j f1 "i Claims. (c1. 2449117) 7 The presentainvention relates to new and use ful improvementsin theconstruction of airplane wings, fuselages, and other parts of an airplane, and has forits. primary object to provide a frame construction for carrying the fabric or covering of the wings, fuselage, and other parts of the airplane. A further object is to provide a frame construction which is strong and durable, relatively inexpensive to manufacture, in which the weight of V V the frame is materially reduced and which at the same time isotherwise well adapted for the purposes for which the same is intended.
Other objects and advantages reside in the details of construction as more fully hereinafter described and claimed, reference being had to the accompanying drawings forming part hereof, wherein like numerals refer to like parts throughout, and in which:
Figure 1 isa fragmentary perspective view of a portion of the frame showing the tube for receiving the fabric covering secured to one of the of a frame member Figure 7 is a transversesectional view thereof.
Figure 8 is a transverse sectional view illustrating the use of the frame construction for a tubular part of an airplane body, such as the fuselage.
Figure 9 is a side elevational view of a modified form of frame construction, with parts broken away.
ber generally which is composed of a pair of metal.
Figure 10 is a fragmentary edge elevational tubes G S,- each-of the tubes being split-longitudinally as shown at 1-1 for receiving-the edge portion-of ametal web memberfl, the edges of the web being inserted through the slots 'lofthe respective-tubes. and" welded to the interior of the tubes at a surface thereof diametrically opposite from the slot '1. Openings 9 are formed in the web 8 to reduce the weight thereof.
When constructing an airplane wing, such as shown in Figures 6 and 7, plurality of fabricretaining tubes ID are welded, as at l l to the top and bottom of the tubes 6, the tubes H3 extending at right angles to the tubes 6 and transversely of the wings. The tubes In at the top and bottom of the wing are preferably connected at the leading trailing edges of the wing. The outer portion of the fabric disposed in the tubes ID. A. handle is may be detachably secured to the strand 7 [4 adjacent its inserted end for guiding the strand through the tubes, the handle 16 being movable along the slots I2.
The longitudinal frame membersof the Wing are designated at H and are constructed of the tubes 6 and web B and the fabric-covering receiving tubes 18 extend transversely thereof and are provided with the longitudinal slots l9' therein for receiving the fabric covering as heretofore explained.
In constructing a fuselage or other tubular body part of the airplane, such as indicated by I the sectional view shown in Figure 8, the frame is designated generally at .26 composed of' the ring-like tubular member 2| having the slot in its outer periphery for receiving the inner edge of a flat ring-like Web 22 and secured therein in a manner as heretofore explained. V
A plurality of openings 23 are formed in the Web adjacent the outer edge thereof, the openings being interrupted to provide communication through said edge. Positioned in the openings are longitudinally extending tubes 24 corresponding to the tubes In and having slots therein registering with the interrupted edge of the openings 23 for receiving the fabric 25 secured" in the tubes by its flexible strand 26.
Figures 9 to 12,.inclusive, represent a modified form of flat frame construction in which the web other edge of the web is inserted into the continuous slot 30 of the tube 3| and suitably secured therein. The tube 3| at its side opposite from the slot '30 is formed with longitudinally spaced slots 32 through which project extensions 33 on the inner end of the web. The extensions are also provided with the openings 34 adapted for receiving the fabric-retaining tubes 35 at the opposite edge of the frame. The tubes 29 and 35 are secured in the openings of the web by welding or in any other suitable manner.
In Figure 13 a curved frame: construction is illustrated embodying the web 36, extension 31, frame tube 38, and fabric-retaining tubes 39 and a 40 at the opposite edges of the web and assem- Having thus described the invention what ll claim is:
1. A frame construction for an airplane com- I receiving the fabric retaining tubes 29 and the prising a ring-like tube having a circumferential slot in its outer periphery, a ring-like web having itsinner edge inserted in said slot and abutting the inner wall of the tube at a point diametrically opposite to the slot, said web having openings adjacent its peripheral edge and having a narrow entrance slot communicating with each opening, and axially extending fabric retaining tubes positioned in said openings and having fabric receiving slots in registry with the entrance slotsof the openings.
2. A frame construction for airplanes comprising a web member having openings adjacent one edge, a tube having a longitudinal slot therein receiving the other edge of the web, said tube also having spaced slots in it side opposite from the first-named slot, extensions on said other edge of the web one of said extensions projecting through .each of the last-named slots outwardly of thetube, said extension also having openings therein, and fabric-retaining tubes positioned in said openings for extending at right angles to the web. I
' JOSEPH K. ANDERSON.
US425476A 1942-01-02 1942-01-02 Airplane construction Expired - Lifetime US2325900A (en)

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2741513A (en) * 1952-05-05 1956-04-10 Lloyd E Dempsey Swing stage platform
US3357533A (en) * 1965-08-06 1967-12-12 Rca Corp Printer having print bars with zigzag struts out of phase
US4355844A (en) * 1979-05-25 1982-10-26 Fiat Auto S.P.A. Skeletal load-bearing structures for motor vehicles
US20080302909A1 (en) * 2007-06-07 2008-12-11 The Boeing Company Cargo roller tray shear fitting

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2741513A (en) * 1952-05-05 1956-04-10 Lloyd E Dempsey Swing stage platform
US3357533A (en) * 1965-08-06 1967-12-12 Rca Corp Printer having print bars with zigzag struts out of phase
US4355844A (en) * 1979-05-25 1982-10-26 Fiat Auto S.P.A. Skeletal load-bearing structures for motor vehicles
US20080302909A1 (en) * 2007-06-07 2008-12-11 The Boeing Company Cargo roller tray shear fitting
US7770844B2 (en) * 2007-06-07 2010-08-10 The Boeing Company Cargo roller tray shear fitting
US20100263193A1 (en) * 2007-06-07 2010-10-21 The Boeing Company Support Beam Shear Fitting
US8056856B2 (en) 2007-06-07 2011-11-15 The Boeing Company Support beam shear fitting

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