GB500076A - Aerofoil structure - Google Patents

Aerofoil structure

Info

Publication number
GB500076A
GB500076A GB1030/38A GB103038A GB500076A GB 500076 A GB500076 A GB 500076A GB 1030/38 A GB1030/38 A GB 1030/38A GB 103038 A GB103038 A GB 103038A GB 500076 A GB500076 A GB 500076A
Authority
GB
United Kingdom
Prior art keywords
segments
wing
members
secured
longitudinally
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
GB1030/38A
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 GB1030/38A priority Critical patent/GB500076A/en
Publication of GB500076A publication Critical patent/GB500076A/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)
  • Aiming, Guidance, Guns With A Light Source, Armor, Camouflage, And Targets (AREA)

Abstract

500,076. Aircraft structures. BARKLEY, A. ST. C. Jan. 12, 1938, No. 1030. [Claes 4] In an aircraft wing structure in which longitudinally-fluted sheet-metal segments are secured together to form a series of closed polygonal or circular passages extending along the wing, longitudinally-extending reinforcing- members are secured to the upper and lower stressed skins of the wing and to the segments. In one form, the segments are flanged at 7 and riveted to the skin 4. A member 9 may be inserted. In further modifications, the segments may be secured to the skin by members 10, Fig. 3, of greater thickness than the segments. The thickness of the members 10 is reduced towards the wing tips. British Specification 482,166 and U.S.A. Specification 2,071,317 are referred to.
GB1030/38A 1938-01-12 1938-01-12 Aerofoil structure Expired GB500076A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB1030/38A GB500076A (en) 1938-01-12 1938-01-12 Aerofoil structure

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1030/38A GB500076A (en) 1938-01-12 1938-01-12 Aerofoil structure

Publications (1)

Publication Number Publication Date
GB500076A true GB500076A (en) 1939-02-02

Family

ID=9714916

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1030/38A Expired GB500076A (en) 1938-01-12 1938-01-12 Aerofoil structure

Country Status (1)

Country Link
GB (1) GB500076A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2203530A (en) * 1987-03-31 1988-10-19 Actionair Equip Shut-off damper
US8087614B2 (en) 2006-06-15 2012-01-03 Airbus Operations Limited Stringer for an aircraft wing and a method of forming thereof

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2203530A (en) * 1987-03-31 1988-10-19 Actionair Equip Shut-off damper
GB2203530B (en) * 1987-03-31 1991-05-01 Actionair Equip Shut-off damper
US8087614B2 (en) 2006-06-15 2012-01-03 Airbus Operations Limited Stringer for an aircraft wing and a method of forming thereof

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