GB654206A - Improvements in and relating to aircraft structures - Google Patents

Improvements in and relating to aircraft structures

Info

Publication number
GB654206A
GB654206A GB27597/48A GB2759748A GB654206A GB 654206 A GB654206 A GB 654206A GB 27597/48 A GB27597/48 A GB 27597/48A GB 2759748 A GB2759748 A GB 2759748A GB 654206 A GB654206 A GB 654206A
Authority
GB
United Kingdom
Prior art keywords
stringers
members
holes
aircraft
transverse members
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
GB27597/48A
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.)
Boulton Paul Aircraft Ltd
Original Assignee
Boulton Paul Aircraft Ltd
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 Boulton Paul Aircraft Ltd filed Critical Boulton Paul Aircraft Ltd
Priority to GB27597/48A priority Critical patent/GB654206A/en
Publication of GB654206A publication Critical patent/GB654206A/en
Expired legal-status Critical Current

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings

Abstract

654,206. Aircraft structures. BOULTON PAUL AIRCRAFT, Ltd., and SMITH, J. F. H. Oct. 23, 1948, No. 27597. [Class 4] An aircraft structural framework, intended to receive an outer load-bearing skin, comprises stiffening members or stringers extending between transverse members such as ribs, formers, or diaphragms, wherein the transverse members are formed with holes of smaller dimensions than will permit the passage therethrough of the stringers, and the latter are joined by coupling-members passing through the holes, whereby the stringers are locked to the transverse members. As shown applied to a wing structure, the stringers 3 are of Z-section and are connected by channel-shaped coupling- members 4, the edges of which engage the peripheries of the holes 5 in the webs of the ribs 1, to give local support to the ends of the stringers. The flanges of the stringers are cut away in the region of each rib to accommodate the flange thereof. Preferably the total crosssectional area of the couplings 4 is not less than that of each stringer. The construction may also be applied to fuselages, control surfaces, or fins.
GB27597/48A 1948-10-23 1948-10-23 Improvements in and relating to aircraft structures Expired GB654206A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB27597/48A GB654206A (en) 1948-10-23 1948-10-23 Improvements in and relating to aircraft structures

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB27597/48A GB654206A (en) 1948-10-23 1948-10-23 Improvements in and relating to aircraft structures

Publications (1)

Publication Number Publication Date
GB654206A true GB654206A (en) 1951-06-13

Family

ID=10262213

Family Applications (1)

Application Number Title Priority Date Filing Date
GB27597/48A Expired GB654206A (en) 1948-10-23 1948-10-23 Improvements in and relating to aircraft structures

Country Status (1)

Country Link
GB (1) GB654206A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160288899A1 (en) * 2015-04-01 2016-10-06 The Boeing Company Composite Rib for an Aircraft

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20160288899A1 (en) * 2015-04-01 2016-10-06 The Boeing Company Composite Rib for an Aircraft
US9849967B2 (en) * 2015-04-01 2017-12-26 The Boeing Company Composite rib for an aircraft

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