GB1497155A - Structures - Google Patents
StructuresInfo
- 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
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).
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)
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 |
-
1975
- 1975-12-22 GB GB477775A patent/GB1497155A/en not_active Expired
Cited By (7)
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 |