GB524721A - Improvements in and relating to "stressed skin" fuselages or nacelles for aircraft - Google Patents

Improvements in and relating to "stressed skin" fuselages or nacelles for aircraft

Info

Publication number
GB524721A
GB524721A GB3767/39A GB376739A GB524721A GB 524721 A GB524721 A GB 524721A GB 3767/39 A GB3767/39 A GB 3767/39A GB 376739 A GB376739 A GB 376739A GB 524721 A GB524721 A GB 524721A
Authority
GB
United Kingdom
Prior art keywords
skin
section
secured
members
aircraft
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
GB3767/39A
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
Publication of GB524721A publication Critical patent/GB524721A/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
    • B64C1/061—Frames
    • 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
    • B64C1/069—Joining arrangements therefor
    • 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
    • B64C2001/0054—Fuselage structures substantially made from particular materials
    • B64C2001/0081—Fuselage structures substantially made from particular materials from metallic materials

Landscapes

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

Abstract

524,721. Aircraft fuselages. AMIOT, F. Feb. 4, 1939, Nos. 3767 and 3768. Convention dates, Feb. 5, 1938 and Jan. 14, 1939. [Class 4] A fuselage or nacelle for aircraft is built up of sections each comprising a stressed skin mounted on a framework of transverse and longitudinal elements, the various sections being united end to end by means of rims secured to the skin and to the longitudinal elements so as to give mechanical and surface continuity. Each section comprises a skin 5 secured to Z-section longitudinal elements 4 and to transverse frames 12, Fig. 8, which are cut to embrace the longitudinal members 4 to which they are secured by brackets 15. Intermediate rings 13, Fig. 9, are secured to the members 4 by brackets 17. The ends of each section have L-members 7, Fig. 3, secured to the skin and to brackets 10 which are riveted to the longitudinal members 4, and adjacent sections are secured together by bolts 8 passing through the radial flanges of the members 7. Fig. 10 shows a modification in which, in addition to end rims 19, the skin of one section overlaps and is riveted to a recessed portion of the skin of the adjacent section. To facilitate assembly longitudinal members may project from one section to engage within an adjacent section.
GB3767/39A 1938-02-05 1939-02-04 Improvements in and relating to "stressed skin" fuselages or nacelles for aircraft Expired GB524721A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
LU524721X 1938-02-05

Publications (1)

Publication Number Publication Date
GB524721A true GB524721A (en) 1940-08-13

Family

ID=19732852

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3767/39A Expired GB524721A (en) 1938-02-05 1939-02-04 Improvements in and relating to "stressed skin" fuselages or nacelles for aircraft

Country Status (1)

Country Link
GB (1) GB524721A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2504421A (en) * 1946-04-25 1950-04-18 Lockheed Aircraft Corp Aircraft engine and fuselage arrangement
US2540482A (en) * 1946-10-01 1951-02-06 Hervey Foundation Inc Wooden structure and method
GB2295999A (en) * 1994-12-16 1996-06-19 British Aerospace Aircraft fuselage manufacture
FR2906008A1 (en) * 2006-09-15 2008-03-21 Airbus France Sa SMOOTH CHEST AND ORBITAL JUNCTION DEVICE
US7938367B2 (en) * 2007-01-02 2011-05-10 Airbus France Stringers assembled at a circumferential joint of an airplane fuselage
JP2012066818A (en) * 2004-09-23 2012-04-05 Boeing Co:The Splice joint for composite aircraft fuselage and other structure
FR2976916A1 (en) * 2011-06-27 2012-12-28 Airbus Operations Sas DEVICE AND METHOD FOR ASSEMBLING TWO TRUNCONS OF AIRCRAFT FUSELAGE
EP2759467A1 (en) * 2013-01-24 2014-07-30 Airbus Operations GmbH Aircraft frame
US9359090B2 (en) 2009-05-12 2016-06-07 Airbus Operations Gmbh Method for producing an aircraft fuselage and aircraft fuselage
CN108202857A (en) * 2016-12-16 2018-06-26 空中客车西班牙运营有限责任公司 Including having the aircraft of the rear portion section of the continuous covering for fuselage and vertical empennage

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2504421A (en) * 1946-04-25 1950-04-18 Lockheed Aircraft Corp Aircraft engine and fuselage arrangement
US2540482A (en) * 1946-10-01 1951-02-06 Hervey Foundation Inc Wooden structure and method
GB2295999A (en) * 1994-12-16 1996-06-19 British Aerospace Aircraft fuselage manufacture
JP2012066818A (en) * 2004-09-23 2012-04-05 Boeing Co:The Splice joint for composite aircraft fuselage and other structure
FR2906008A1 (en) * 2006-09-15 2008-03-21 Airbus France Sa SMOOTH CHEST AND ORBITAL JUNCTION DEVICE
US7823362B2 (en) 2006-09-15 2010-11-02 Airbus France Splice plate for stringers and orbital joining device
US7938367B2 (en) * 2007-01-02 2011-05-10 Airbus France Stringers assembled at a circumferential joint of an airplane fuselage
EP2429894B1 (en) * 2009-05-12 2016-11-23 Airbus Operations GmbH Method for producing an aircraft fuselage and aircraft fuselage
US9359090B2 (en) 2009-05-12 2016-06-07 Airbus Operations Gmbh Method for producing an aircraft fuselage and aircraft fuselage
EP2540615A1 (en) * 2011-06-27 2013-01-02 Airbus Operations (Société par actions simplifiée) Device and method for assembling two aircraft fuselage sections
FR2976916A1 (en) * 2011-06-27 2012-12-28 Airbus Operations Sas DEVICE AND METHOD FOR ASSEMBLING TWO TRUNCONS OF AIRCRAFT FUSELAGE
US10150553B2 (en) 2011-06-27 2018-12-11 Airbus Operations (Societe Par Actions Simplifiee) Device and method for assembling two sections of aircraft fuselage
EP2759467A1 (en) * 2013-01-24 2014-07-30 Airbus Operations GmbH Aircraft frame
CN103963955A (en) * 2013-01-24 2014-08-06 空中客车德国运营有限责任公司 Aircraft frame
US9511845B2 (en) 2013-01-24 2016-12-06 Airbus Operations Gmbh Aircraft frame
CN108202857A (en) * 2016-12-16 2018-06-26 空中客车西班牙运营有限责任公司 Including having the aircraft of the rear portion section of the continuous covering for fuselage and vertical empennage
CN108202857B (en) * 2016-12-16 2022-10-04 空中客车西班牙运营有限责任公司 Aircraft comprising an aft section with a continuous skin for the fuselage and vertical tail

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