GB140113A - Improvements in the framework of aircraft and the like - Google Patents

Improvements in the framework of aircraft and the like

Info

Publication number
GB140113A
GB140113A GB668418A GB668418A GB140113A GB 140113 A GB140113 A GB 140113A GB 668418 A GB668418 A GB 668418A GB 668418 A GB668418 A GB 668418A GB 140113 A GB140113 A GB 140113A
Authority
GB
United Kingdom
Prior art keywords
spar
framework
tensioning
receive
devices
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
GB668418A
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.)
Individual
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to GB668418A priority Critical patent/GB140113A/en
Publication of GB140113A publication Critical patent/GB140113A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/18—Spars; Ribs; Stringers

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Rod-Shaped Construction Members (AREA)

Abstract

140,113. Page, F. H. April 20, 1918. Framework.-Tension wires are attached to aircraft struts, spars, &c. by means of a tubular bushing passing through the strut &c. at its neutral axis and having its walls perforated to receive the tension wires. Fig. 1 shows bracing-wires 4, 5 fitted with tensioning-devices 11 which pass through the walls of the tubular bush 3 on the spar 1. Plates 9 of ply wood, metal, &c., strengthened by ribs 6, may be applied on each side of the spar. The central wire 4 passes through a hole 12 in the spar. The bushing 3 contains segmental stiffening-elements 13 threaded to receive the tensioning-devices 11.
GB668418A 1918-04-20 1918-04-20 Improvements in the framework of aircraft and the like Expired GB140113A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB668418A GB140113A (en) 1918-04-20 1918-04-20 Improvements in the framework of aircraft and the like

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB668418A GB140113A (en) 1918-04-20 1918-04-20 Improvements in the framework of aircraft and the like

Publications (1)

Publication Number Publication Date
GB140113A true GB140113A (en) 1920-03-25

Family

ID=9818907

Family Applications (1)

Application Number Title Priority Date Filing Date
GB668418A Expired GB140113A (en) 1918-04-20 1918-04-20 Improvements in the framework of aircraft and the like

Country Status (1)

Country Link
GB (1) GB140113A (en)

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