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On the use of non traditional stacking to maximize critical buckling loads in flat composite panels.
- Source :
-
Composite Structures . Apr2021, Vol. 261, pN.PAG-N.PAG. 1p. - Publication Year :
- 2021
-
Abstract
- Traditional lay-ups in laminated composite structural parts have largely focused on using quasi-isotropic laminates made of permutations of 0 ° , 90 ° and ± 45 ° laminae. These laminates are referred to as legacy quad laminates (LQL). In this study, three different lay-ups of symmetric laminates to compute critical buckling loads under uniaxial in-plane compressive loads is first investigated. An optimization problem is solved to determine the lay-ups that maximize the buckling performance. The resulting laminates are compared against a new class of laminates, referred to as double-double (DD), which have distinctive advantages for thickness tapering and therefore manufacturability. Both, symmetric and unsymmetric DD laminates are studied, while in the latter case, a thermal cure cycle followed by the application of in-plane loads is used to determine the structural performance in compression. To further verify the versatility of DD laminates, biaxial buckling loads are computed for quad, DD and optimized lay-ups. It is concluded that DD laminates, because of their manufacturability advantages, are promising candidates for several aerostructural applications. [ABSTRACT FROM AUTHOR]
- Subjects :
- *LAMINATED materials
*COMPRESSION loads
*MECHANICAL buckling
*THERMOCYCLING
Subjects
Details
- Language :
- English
- ISSN :
- 02638223
- Volume :
- 261
- Database :
- Academic Search Index
- Journal :
- Composite Structures
- Publication Type :
- Academic Journal
- Accession number :
- 148731242
- Full Text :
- https://doi.org/10.1016/j.compstruct.2020.113320