GB193880A - Improvements in aircraft - Google Patents

Improvements in aircraft

Info

Publication number
GB193880A
GB193880A GB22819/21A GB2281921A GB193880A GB 193880 A GB193880 A GB 193880A GB 22819/21 A GB22819/21 A GB 22819/21A GB 2281921 A GB2281921 A GB 2281921A GB 193880 A GB193880 A GB 193880A
Authority
GB
United Kingdom
Prior art keywords
wing
braced
spars
girder
wires
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
GB22819/21A
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.)
INTERNAT ALL STEEL AIRCRAFT SY
Original Assignee
INTERNAT ALL STEEL AIRCRAFT SY
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 INTERNAT ALL STEEL AIRCRAFT SY filed Critical INTERNAT ALL STEEL AIRCRAFT SY
Priority to GB22819/21A priority Critical patent/GB193880A/en
Publication of GB193880A publication Critical patent/GB193880A/en
Expired legal-status Critical Current

Links

Classifications

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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Bridges Or Land Bridges (AREA)

Abstract

193,880. International All- Steel Aircraft Syndicate, Ltd., Bolas, H., and Parnall, G. G. Aug. 29, 1921. Cars; planes, construction of.-The structure of the wings, or of a body which is in the form of a pterygoid aerofoil, comprises a braced girder in the front half of the structure. The figure shows a wing in which the front girder comprises two front spars braced by wires 7, 8. Bracing wires 12, 13 may also pass from the top of the spar 2 to the bottom of the rear spar 4 to distribute the loading and to avoid fouling intermediate spars. The wing shown may be connected to a stub wing at 1<a> - - 4<a>.
GB22819/21A 1921-08-29 1921-08-29 Improvements in aircraft Expired GB193880A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB22819/21A GB193880A (en) 1921-08-29 1921-08-29 Improvements in aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB22819/21A GB193880A (en) 1921-08-29 1921-08-29 Improvements in aircraft

Publications (1)

Publication Number Publication Date
GB193880A true GB193880A (en) 1923-02-28

Family

ID=10185555

Family Applications (1)

Application Number Title Priority Date Filing Date
GB22819/21A Expired GB193880A (en) 1921-08-29 1921-08-29 Improvements in aircraft

Country Status (1)

Country Link
GB (1) GB193880A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2563422A (en) * 2017-06-15 2018-12-19 Airbus Operations Ltd A spar arrangement in a wing tip device

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2563422A (en) * 2017-06-15 2018-12-19 Airbus Operations Ltd A spar arrangement in a wing tip device
US11643183B2 (en) 2017-06-15 2023-05-09 Airbus Operations Limited Spar arrangement in a wing tip device
US11958597B2 (en) 2017-06-15 2024-04-16 Airbus Operations Limited Spar arrangement in a wing tip device

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