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- Article name
- Design, fabrication and testing of an airplane wing composite lattice panel
- Authors
- BABICHEV A. A., , 185@bk.ru, Central Institute of Special Machinery, Khotkovo, Moscow region, Russia
VASILIEV V. V., , vvvas@dol.ru, Central Institute of Special Machinery, Khotkovo, Moscow region, Russia
RAZIN A. F., , tsniism@tsniism.ru, Central Institute of Special Machinery, Khotkovo, Moscow region, Russia
AZAROV A. V., , avazar@bk.ru, Central Research Institute for Special Machinery; Bauman Moscow State Technical University, Khot'kovo, Moscow Region, Russia; Moscow, Russia
- Keywords
- composite materials / lattice structures / optimal design / testing
- Year
- 2025 Issue 1 Pages 10 - 16
- Code EDN
- CCQKFZ
- Code DOI
- 10.52190/2073-2562_2025_1_10
- Abstract
- The article reviews is concerned with design of a flat rectangular panel consisting of a system of intersecting ribs made of unidirectional composite material by filament winding or lay-up processes. The panel is a structural element of an airplane wing. The panel is simply supported and compressed in the longitudinal direction. The relations which specify the optimal structural parameters of the lattice panel, i.e., the panel thickness, the ribs orientation angle, the ribs thickness and spacing are obtained. The optimal parameters provide the panel minimum mass under strength and buckling constraints. Optimization is undertaken by the method of minimization of the safety factors corresponding to possible modes of the panel failure. The method allows us to reduce the constrained optimization problem to the problem of conditional minimization. The results of design, analysis and testing under longitudinal compression are presented for the experimental panel consisting of a system of longitudinal and diagonal ribs.
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