Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego
A section of fuselage skin with dimension 30 x 200 mm was subjected to numerical study and loaded by skew bending (Fig. 3). The thickness of the skin was 0,6 mm, the length of a leg of an angle “L” profile stringer was 12 mm with 1mm thickness. The angle of inclination α of the load plane to the ski...
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| Format: | Article |
| Language: | English |
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Polish Academy of Sciences
2015-12-01
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| Series: | Archives of Metallurgy and Materials |
| Subjects: | |
| Online Access: | http://www.degruyter.com/view/j/amm.2015.60.issue-4/amm-2015-0451/amm-2015-0451.xml?format=INT |
| _version_ | 1828258245263753216 |
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| author | Sadowski T. Golewski P. |
| author_facet | Sadowski T. Golewski P. |
| author_sort | Sadowski T. |
| collection | DOAJ |
| description | A section of fuselage skin with dimension 30 x 200 mm was subjected to numerical study and loaded by skew bending (Fig. 3). The thickness of the skin was 0,6 mm, the length of a leg of an angle “L” profile stringer was 12 mm with 1mm thickness. The angle of inclination α of the load plane to the skin plane varies in the range from 10° to 90° with 10° increment. The elastic - plastic material model of D16T aluminum alloy was used in simulations of the fuselage skin as well as for “L” and “C” profile stringers. In the material model description damage of aluminum alloy was taken into account. An adhesive layer with thickness of 0,1mm was modeled using cohesive elements with the failure mode depending on the shear strength and the tensile strength. |
| first_indexed | 2024-04-13T02:51:33Z |
| format | Article |
| id | doaj.art-bfbd608fd9514be3aa61619680374aa8 |
| institution | Directory Open Access Journal |
| issn | 2300-1909 |
| language | English |
| last_indexed | 2024-04-13T02:51:33Z |
| publishDate | 2015-12-01 |
| publisher | Polish Academy of Sciences |
| record_format | Article |
| series | Archives of Metallurgy and Materials |
| spelling | doaj.art-bfbd608fd9514be3aa61619680374aa82022-12-22T03:05:50ZengPolish Academy of SciencesArchives of Metallurgy and Materials2300-19092015-12-016042813282010.1515/amm-2015-0451amm-2015-0451Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza HybrydowegoSadowski T.0Golewski P.1LUBLIN UNIVERSITY OF TECHNOLOGY, 40 NADBYSTRZYCKA STR., 20-618 LUBLIN, POLANDLUBLIN UNIVERSITY OF TECHNOLOGY, 40 NADBYSTRZYCKA STR., 20-618 LUBLIN, POLANDA section of fuselage skin with dimension 30 x 200 mm was subjected to numerical study and loaded by skew bending (Fig. 3). The thickness of the skin was 0,6 mm, the length of a leg of an angle “L” profile stringer was 12 mm with 1mm thickness. The angle of inclination α of the load plane to the skin plane varies in the range from 10° to 90° with 10° increment. The elastic - plastic material model of D16T aluminum alloy was used in simulations of the fuselage skin as well as for “L” and “C” profile stringers. In the material model description damage of aluminum alloy was taken into account. An adhesive layer with thickness of 0,1mm was modeled using cohesive elements with the failure mode depending on the shear strength and the tensile strength.http://www.degruyter.com/view/j/amm.2015.60.issue-4/amm-2015-0451/amm-2015-0451.xml?format=INTskew bending of hybrid jointdeformation processesFEA (finite element analysis) |
| spellingShingle | Sadowski T. Golewski P. Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego Archives of Metallurgy and Materials skew bending of hybrid joint deformation processes FEA (finite element analysis) |
| title | Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego |
| title_full | Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego |
| title_fullStr | Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego |
| title_full_unstemmed | Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego |
| title_short | Skew Bending of Aircraft Fuselage Panels with “L” and “C” Stringers Mounted by Hybrid Joint / Ukośne Zginanie Poszycia Samolotu Z U Sztywnieniami Typu “L” I “C”, Mocowanymi Za Pomocą Złącza Hybrydowego |
| title_sort | skew bending of aircraft fuselage panels with l and c stringers mounted by hybrid joint ukosne zginanie poszycia samolotu z u sztywnieniami typu l i c mocowanymi za pomoca zlacza hybrydowego |
| topic | skew bending of hybrid joint deformation processes FEA (finite element analysis) |
| url | http://www.degruyter.com/view/j/amm.2015.60.issue-4/amm-2015-0451/amm-2015-0451.xml?format=INT |
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