GB520249A - Improvements in stressed-skin structures of fuselages, wings and other hollow bodies of aircraft - Google Patents

Improvements in stressed-skin structures of fuselages, wings and other hollow bodies of aircraft

Info

Publication number
GB520249A
GB520249A GB29937/38A GB2993738A GB520249A GB 520249 A GB520249 A GB 520249A GB 29937/38 A GB29937/38 A GB 29937/38A GB 2993738 A GB2993738 A GB 2993738A GB 520249 A GB520249 A GB 520249A
Authority
GB
United Kingdom
Prior art keywords
stressed
aircraft
fuselages
wings
hollow bodies
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
GB29937/38A
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 GB29937/38A priority Critical patent/GB520249A/en
Publication of GB520249A publication Critical patent/GB520249A/en
Expired legal-status Critical Current

Links

Classifications

    • 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
    • B64C1/068—Fuselage sections
    • 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
    • B64C1/12—Construction or attachment of skin panels

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Joining Of Building Structures In Genera (AREA)

Abstract

520,249. Aircraft framework. MAYROW, J. J. Oct. 15, 1938, No. 29937. [Class 4] Stressed skin structures are braced by crossing members of suitable section to match the longerons E, Fig. 3, and transverse stringers F, cantilever members A being provided in the angles between the longerons and stringers which are attached to and brace the skin G. Fig. 10 shows a form in which channelled cross members L are provided with cantilever members A<1> extending from one to the other.
GB29937/38A 1938-10-15 1938-10-15 Improvements in stressed-skin structures of fuselages, wings and other hollow bodies of aircraft Expired GB520249A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB29937/38A GB520249A (en) 1938-10-15 1938-10-15 Improvements in stressed-skin structures of fuselages, wings and other hollow bodies of aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB29937/38A GB520249A (en) 1938-10-15 1938-10-15 Improvements in stressed-skin structures of fuselages, wings and other hollow bodies of aircraft

Publications (1)

Publication Number Publication Date
GB520249A true GB520249A (en) 1940-04-18

Family

ID=10299634

Family Applications (1)

Application Number Title Priority Date Filing Date
GB29937/38A Expired GB520249A (en) 1938-10-15 1938-10-15 Improvements in stressed-skin structures of fuselages, wings and other hollow bodies of aircraft

Country Status (1)

Country Link
GB (1) GB520249A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2940785A1 (en) * 2009-01-08 2010-07-09 Airbus France LONGITUDINAL JUNCTION FOR AIRCRAFT FUSELAGE PANELS IN COMPOSITE MATERIALS
JP2011521825A (en) * 2008-05-30 2011-07-28 エアバス オペラツィオンス ゲゼルシャフト ミット ベシュレンクテル ハフツング Composites and structures, especially in the field of aircraft
EP2530010A1 (en) * 2011-06-02 2012-12-05 Bell Helicopter Textron Inc. Integrally stiffened panel
US9896180B2 (en) 2014-05-06 2018-02-20 Airbus Operations Gmbh Method for manufacturing a load bearing structure and such a load bearing structure

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011521825A (en) * 2008-05-30 2011-07-28 エアバス オペラツィオンス ゲゼルシャフト ミット ベシュレンクテル ハフツング Composites and structures, especially in the field of aircraft
FR2940785A1 (en) * 2009-01-08 2010-07-09 Airbus France LONGITUDINAL JUNCTION FOR AIRCRAFT FUSELAGE PANELS IN COMPOSITE MATERIALS
WO2010079282A1 (en) * 2009-01-08 2010-07-15 Airbus Operations (Sas) Longitudinal joint for aircraft fuselage panels made of composite materials
CN102317153A (en) * 2009-01-08 2012-01-11 空中客车营运有限公司 The vertical attaching parts that is used for composite material aircraft fuselage plate
EP2530010A1 (en) * 2011-06-02 2012-12-05 Bell Helicopter Textron Inc. Integrally stiffened panel
CN102806989A (en) * 2011-06-02 2012-12-05 贝尔直升机德事隆公司 Integrally stiffened panel
US8517309B2 (en) 2011-06-02 2013-08-27 Bell Helicopter Textron Inc. Integrally stiffened panel
CN102806989B (en) * 2011-06-02 2015-04-01 贝尔直升机德事隆公司 Integrally stiffened panel
US9896180B2 (en) 2014-05-06 2018-02-20 Airbus Operations Gmbh Method for manufacturing a load bearing structure and such a load bearing structure

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