GB457369A - Improvements in or relating to sheet metal walls and/or partitions for aircraft - Google Patents

Improvements in or relating to sheet metal walls and/or partitions for aircraft

Info

Publication number
GB457369A
GB457369A GB9410/36A GB941036A GB457369A GB 457369 A GB457369 A GB 457369A GB 9410/36 A GB9410/36 A GB 9410/36A GB 941036 A GB941036 A GB 941036A GB 457369 A GB457369 A GB 457369A
Authority
GB
United Kingdom
Prior art keywords
members
aircraft
partitions
relating
sheet metal
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
GB9410/36A
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.)
Dornier Metallbauten GmbH
Original Assignee
Dornier Metallbauten GmbH
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 Dornier Metallbauten GmbH filed Critical Dornier Metallbauten GmbH
Publication of GB457369A publication Critical patent/GB457369A/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
    • B64C1/12—Construction or attachment of skin panels
    • 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)
  • Laminated Bodies (AREA)

Abstract

457,369. Aircraft framework. DORNIER METALLBAUTEN GES., Friedrichshafen, Germany. March 30, 1936, No. 9410. Convention date, June 29, 1935. [Class 4] [See also Group X] In a sheet-metal wall or partition 1 for aircraft having on one side laterally flanged strengthening members 2, 3 having in section a U-shaped profile, the members are joined together at their points of intersection by cross-connectors or straps 4, the arms of which are shaped to conform to the shape of the profiled reinforcing members 2, 3. Where one profiled section reinforcing member is at a different level from the other, the arms of the cross straps are arranged at different heights. The flanges of the members 3 are flattened out at the points of intersection with the members 2.
GB9410/36A 1935-06-29 1936-03-30 Improvements in or relating to sheet metal walls and/or partitions for aircraft Expired GB457369A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE457369X 1935-06-29

Publications (1)

Publication Number Publication Date
GB457369A true GB457369A (en) 1936-11-26

Family

ID=6539306

Family Applications (1)

Application Number Title Priority Date Filing Date
GB9410/36A Expired GB457369A (en) 1935-06-29 1936-03-30 Improvements in or relating to sheet metal walls and/or partitions for aircraft

Country Status (1)

Country Link
GB (1) GB457369A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2009146958A1 (en) * 2008-05-30 2009-12-10 Airbus Operations Gmbh Composite and structure, particularly in the aerospace sector
JP2011500415A (en) * 2007-10-18 2011-01-06 エアバス オペレーションズ （エスアーエス） Aircraft having a stiffener end connection and a method of manufacturing such an aircraft
US9896180B2 (en) 2014-05-06 2018-02-20 Airbus Operations Gmbh Method for manufacturing a load bearing structure and such a load bearing structure
FR3129203A1 (en) * 2021-11-18 2023-05-19 Safran Nacelles Rigid open composite panel

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2011500415A (en) * 2007-10-18 2011-01-06 エアバス オペレーションズ （エスアーエス） Aircraft having a stiffener end connection and a method of manufacturing such an aircraft
WO2009146958A1 (en) * 2008-05-30 2009-12-10 Airbus Operations Gmbh Composite and structure, particularly in the aerospace sector
CN102046358A (en) * 2008-05-30 2011-05-04 空中客车运营有限公司 Composite and structure, particularly in the aerospace sector
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
US8403263B2 (en) 2008-05-30 2013-03-26 Airbus Operations Gmbh Composite and structure, particularly in the aerospace sector
CN102046358B (en) * 2008-05-30 2013-07-31 空中客车运营有限公司 Composite and structure, particularly in the aerospace sector
RU2496678C2 (en) * 2008-05-30 2013-10-27 Эйрбас Оперэйшнз Гмбх Structural assembly and structure used, in particular, in aircraft engineering
DE102008002117B4 (en) * 2008-05-30 2013-10-31 Airbus Operations Gmbh Composite and structure
US9896180B2 (en) 2014-05-06 2018-02-20 Airbus Operations Gmbh Method for manufacturing a load bearing structure and such a load bearing structure
FR3129203A1 (en) * 2021-11-18 2023-05-19 Safran Nacelles Rigid open composite panel
WO2023089273A1 (en) * 2021-11-18 2023-05-25 Safran Nacelles Rigid open composite panel

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