Composite material wing structure optimization method based on topological optimization

The invention discloses a composite material wing structure optimization method based on topological optimization, and the method comprises the steps: carrying out the preliminary optimization through employing a topological optimization method based on a finite element model of a target structure,...

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Bibliographic Details
Main Authors TIAN XIAO, HOU JUNPING, KANG JIANXIONG, LI NA, CAO YAQI, GUO WEIXING
Format Patent
LanguageChinese
English
Published 26.01.2024
Subjects
CALCULATING
COMPUTING
COUNTING
ELECTRIC DIGITAL DATA PROCESSING
PHYSICS
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Summary:The invention discloses a composite material wing structure optimization method based on topological optimization, and the method comprises the steps: carrying out the preliminary optimization through employing a topological optimization method based on a finite element model of a target structure, enabling the optimization target to be the minimum structural strain energy, and enabling the optimization constraint to be the size of a design target region; static strength checking is conducted on the topological optimization result through the maximum strain criterion, then stability checking is conducted on the finite element model of the topological optimization result, if static strength checking or stability checking is not passed, optimization volume constraint is reset, topological optimization is conducted again, and iteration is conducted till the optimization result meets the requirement of multi-layer constraint. The weight of the solar unmanned aerial vehicle wing structure is effectively reduced. 本
Bibliography:Application Number: CN202210841666