GB365280A - Improvements in or connected with sheet metal spars particularly adapted for use in aircraft structures - Google Patents

Improvements in or connected with sheet metal spars particularly adapted for use in aircraft structures

Info

Publication number
GB365280A
GB365280A GB38440/30A GB3844030A GB365280A GB 365280 A GB365280 A GB 365280A GB 38440/30 A GB38440/30 A GB 38440/30A GB 3844030 A GB3844030 A GB 3844030A GB 365280 A GB365280 A GB 365280A
Authority
GB
United Kingdom
Prior art keywords
strips
booms
edges
rivets
struts
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
Application number
GB38440/30A
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.)
STEEL WING Co Ltd
Original Assignee
STEEL WING Co Ltd
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 STEEL WING Co Ltd filed Critical STEEL WING Co Ltd
Priority to GB38440/30A priority Critical patent/GB365280A/en
Publication of GB365280A publication Critical patent/GB365280A/en
Expired legal-status Critical Current

Links

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
    • B64C1/065Spars
    • 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
    • YGENERAL 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
    • Y02TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02TCLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00Aeronautics or air transport
    • Y02T50/40Weight reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Connection Of Plates (AREA)

Abstract

365,280. Metal spars for aircraft. STEEL WING CO., Ltd., Gloster Works & Aerodrome, Hucclecote, and EMBY, D. H., Old Vicarage, Ampney Crucis, near Cirencester, both in Gloucestershire. Dec. 20, 1930, Nos. 38440/30 and 25833/31. [Class 4.] Metal spars for aircraft have booms formed from two or more metal strips so corrugated and bent that the borders of the strips coincide and are fixed together while other parts of the strips are spaced apart, two such looms being connected together by distancing struts and diagonal bracing embraced by the outer borders of the booms. Fig. 1 shows a spar having booms each formed from two strips a, b having coterminal edges a3, a4 and central portions a<5> with intermediate portions spaced as shown. The edges a<3>, a<4> and central portions a<5> are secured together by hollow rivets those securing the former passing through spacing tubes. Vertical struts c bent as shown and provided with liners c<6> at their ends are secured to the edges a<3>, a<4> by bolts d passing through distance tubes d<1> or by separate rivets. Diagonal bracing e of channel section expanded at the ends and fitted with strengthening pieces e<2> are secured to the booms also by the bolts d or rivets which secure the struts. Lightening holes c<5> are formed in the struts c. Various modified booms are described. The strip a may be in two parts with flat overlapping central portions, upturned at the edges to interengage, or the strip b may be of channel section with rounded corners, or strips with polygonal instead of curved corrugations may be used. Fig. 8 shows a boom made from four pieces overlapping at the centre and Fig. 9 a boom made with three strips two of which fit closely together. A boom formed from two strips so bent as to form rectangular hollow spaces at the corners also is described with an additional strip secured over the central flat portion. Figs. 10 and 12 show other modifications. The spacing of the rivets bracing the edges a<3>, a<4> together is varied to suit the load on the spar and the thickness or number of the strips forming a boom may be varied for the same purpose.
GB38440/30A 1930-12-20 1930-12-20 Improvements in or connected with sheet metal spars particularly adapted for use in aircraft structures Expired GB365280A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB38440/30A GB365280A (en) 1930-12-20 1930-12-20 Improvements in or connected with sheet metal spars particularly adapted for use in aircraft structures

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB38440/30A GB365280A (en) 1930-12-20 1930-12-20 Improvements in or connected with sheet metal spars particularly adapted for use in aircraft structures

Publications (1)

Publication Number Publication Date
GB365280A true GB365280A (en) 1932-01-21

Family

ID=10403451

Family Applications (1)

Application Number Title Priority Date Filing Date
GB38440/30A Expired GB365280A (en) 1930-12-20 1930-12-20 Improvements in or connected with sheet metal spars particularly adapted for use in aircraft structures

Country Status (1)

Country Link
GB (1) GB365280A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2448362A (en) * 1945-09-26 1948-08-31 Beech Aircraft Corp Aircraft beam chord construction
DE3427901A1 (en) * 1984-07-28 1986-02-06 Dyckerhoff & Widmann AG, 8000 München Method for manufacturing a multipart ring wedge of a wedge anchoring for a prestressing element in a concrete structural part

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2448362A (en) * 1945-09-26 1948-08-31 Beech Aircraft Corp Aircraft beam chord construction
DE3427901A1 (en) * 1984-07-28 1986-02-06 Dyckerhoff & Widmann AG, 8000 München Method for manufacturing a multipart ring wedge of a wedge anchoring for a prestressing element in a concrete structural part

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