GB1497155A - Structures - Google Patents

Structures

Info

Publication number
GB1497155A
GB1497155A GB477775A GB477775A GB1497155A GB 1497155 A GB1497155 A GB 1497155A GB 477775 A GB477775 A GB 477775A GB 477775 A GB477775 A GB 477775A GB 1497155 A GB1497155 A GB 1497155A
Authority
GB
United Kingdom
Prior art keywords
tube
crack
strip
strips
zig
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
GB477775A
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.)
Secretary of State for Defence Canada
UK Secretary of State for Defence
Original Assignee
Secretary of State for Defence Canada
UK Secretary of State for Defence
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 Secretary of State for Defence Canada, UK Secretary of State for Defence filed Critical Secretary of State for Defence Canada
Priority to GB477775A priority Critical patent/GB1497155A/en
Publication of GB1497155A publication Critical patent/GB1497155A/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

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Reinforced Plastic Materials (AREA)

Abstract

1497155 Aircraft structures DEFENCE SECRETARY OF STATE FOR 22 Dec 1975 [4 Feb 1975] 4777/75 Heading B7W An aircraft structure comprises a skin 10 and parallel rectangular tubes 11 secured to the skin, and to prevent the growth of a crack (15), Fig. 3 (not shown), in the structure a sinusoidal strip 13 is contained within each tube. Each strip is formed of carbon-fibre-reinforced cured plastics and when contained in the tube is constricted so as to require a force to pull it out of the tube. The force is of the order of 50% of the ultimate tensile strength of the strip and tends to resist the spread of a crack extending transversely of the tube. The longer the crack becomes the more strips come into effect and apply resisting forces to the crack. The strips have a cross-sectional area of about 3% of the cross-sectional area of the whole structure. The strips may alternatively be of zig-zag form or a combination of zig-zag and sinusoidal form. The tubes have integral frames (21), Fig. 1 (not shown).
GB477775A 1975-12-22 1975-12-22 Structures Expired GB1497155A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB477775A GB1497155A (en) 1975-12-22 1975-12-22 Structures

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB477775A GB1497155A (en) 1975-12-22 1975-12-22 Structures

Publications (1)

Publication Number Publication Date
GB1497155A true GB1497155A (en) 1978-01-05

Family

ID=9783626

Family Applications (1)

Application Number Title Priority Date Filing Date
GB477775A Expired GB1497155A (en) 1975-12-22 1975-12-22 Structures

Country Status (1)

Country Link
GB (1) GB1497155A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0048191A1 (en) * 1980-09-09 1982-03-24 Aerospatiale Societe Nationale Industrielle Airship fuselage structure resistant to longitudinal cracks of the skin
FR2574472A1 (en) * 1984-12-08 1986-06-13 Rolls Royce RETAINER FOR ROTOR BLADE
CN102372084A (en) * 2010-07-08 2012-03-14 空中客车运营公司 Method for realization of an aircraft structure and resulting structure
EP2508419A1 (en) * 2011-04-05 2012-10-10 Airbus Opérations SAS Method of slowing the propagation of cracks in a fail safe structure and fail safe frame, especially for fuselage
CN104870307A (en) * 2012-12-21 2015-08-26 空中客车运营简化股份公司 Aircraft fuselage stiffener formed from a sheet folded over onto itself

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0048191A1 (en) * 1980-09-09 1982-03-24 Aerospatiale Societe Nationale Industrielle Airship fuselage structure resistant to longitudinal cracks of the skin
FR2574472A1 (en) * 1984-12-08 1986-06-13 Rolls Royce RETAINER FOR ROTOR BLADE
CN102372084A (en) * 2010-07-08 2012-03-14 空中客车运营公司 Method for realization of an aircraft structure and resulting structure
EP2508419A1 (en) * 2011-04-05 2012-10-10 Airbus Opérations SAS Method of slowing the propagation of cracks in a fail safe structure and fail safe frame, especially for fuselage
FR2973773A1 (en) * 2011-04-05 2012-10-12 Airbus Operations Sas METHOD FOR SLOWING THE PROPAGATION OF CRACKS IN A SECURE STRUCTURE AND A HIGHLY SECURE FRAME, ESPECIALLY A FUSELAGE
US8708281B2 (en) 2011-04-05 2014-04-29 Airbus Operations (Sas) Method of slowing the propagation of cracks in a fail safe structure and fail safe frame, especially for fuselage
CN104870307A (en) * 2012-12-21 2015-08-26 空中客车运营简化股份公司 Aircraft fuselage stiffener formed from a sheet folded over onto itself

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Legal Events

Date Code Title Description
PS Patent sealed
732 Registration of transactions, instruments or events in the register (sect. 32/1977)
PCNP Patent ceased through non-payment of renewal fee