TY - GEN
T1 - Design factors for anisotropic composite cylindrical shells subject to compression buckling on elastic foundations
AU - Ansari, Quaiyum M.
AU - Zucco, Giovanni
AU - Trinh, Luan C.
AU - Weaver, Paul M.
N1 - Publisher Copyright:
© 2021, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved.
PY - 2021
Y1 - 2021
N2 - Composite cylindrical shells are widely used in space launch systems due to their high load-carrying capability and also for being light weight. However, these structures are prone to buckle at a much lower load than classical predictions for the perfect cylinder. In literature, the effect of geometrical imperfections on the buckling response of thin-walled cylindrical shells has received considerable attention. However, only a few works have addressed the effect of boundary conditions on the buckling behavior of these structures. The detrimental effect of boundary conditions along with inherent material anisotropy could lead to a 60% reduction in buckling load providing a need for detailed studies in this area. Therefore, refined theoretical models and design factors are sought to address practical preliminary design issues. The main aim of this work is to understand the effect of bend-twist anisotropy on buckling of homogenized, quasi-isotropic cylindrical shells on elastic foundations and develop empirical relations that could possibly help designers to quickly estimate buckling loads without using finite element analysis. To do so, the critical buckling load for homogenized quasi-isotropic thin-walled cylindrical shells on elastic foundations with low, medium and high levels of bend-twist anisotropy are investigated. Finally, an analysis-driven design approach is proposed to estimate upper and lower critical buckling load and knockdown factor expressions are given for axial, radial, and tangential elastic foundations.
AB - Composite cylindrical shells are widely used in space launch systems due to their high load-carrying capability and also for being light weight. However, these structures are prone to buckle at a much lower load than classical predictions for the perfect cylinder. In literature, the effect of geometrical imperfections on the buckling response of thin-walled cylindrical shells has received considerable attention. However, only a few works have addressed the effect of boundary conditions on the buckling behavior of these structures. The detrimental effect of boundary conditions along with inherent material anisotropy could lead to a 60% reduction in buckling load providing a need for detailed studies in this area. Therefore, refined theoretical models and design factors are sought to address practical preliminary design issues. The main aim of this work is to understand the effect of bend-twist anisotropy on buckling of homogenized, quasi-isotropic cylindrical shells on elastic foundations and develop empirical relations that could possibly help designers to quickly estimate buckling loads without using finite element analysis. To do so, the critical buckling load for homogenized quasi-isotropic thin-walled cylindrical shells on elastic foundations with low, medium and high levels of bend-twist anisotropy are investigated. Finally, an analysis-driven design approach is proposed to estimate upper and lower critical buckling load and knockdown factor expressions are given for axial, radial, and tangential elastic foundations.
UR - http://www.scopus.com/inward/record.url?scp=85100308489&partnerID=8YFLogxK
M3 - Conference contribution
AN - SCOPUS:85100308489
SN - 9781624106095
T3 - AIAA Scitech 2021 Forum
SP - 1
EP - 17
BT - AIAA Scitech 2021 Forum
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - AIAA Science and Technology Forum and Exposition, AIAA SciTech Forum 2021
Y2 - 11 January 2021 through 15 January 2021
ER -