New biomimetic approach to the aircraft wing structural design based on aeroelastic analysis

Bulletin of the Polish Academy of Sciences. Technical Sciences

R. RoszakChair of Virtual Engineering, Poznan University of Technology, 24 Jana Pawla II, 60-965 Poznan, PolandOther articles by this author:De Gruyter OnlineGoogle Scholar¹  M. NowakChair of Virtual Engineering, Poznan University of Technology, 24 Jana Pawla II, 60-965 Poznan, PolandOther articles by this author:De Gruyter OnlineGoogle Scholar¹  D. GawelCorresponding authorChair of Virtual Engineering, Poznan University of Technology, 24 Jana Pawla II, 60-965 Poznan, PolandEmailOther articles by this author:De Gruyter OnlineGoogle Scholar¹  H. HausaChair of Virtual Engineering, Poznan University of Technology, 24 Jana Pawla II, 60-965 Poznan, PolandOther articles by this author:De Gruyter OnlineGoogle Scholar¹ 

[1] Chair of Virtual Engineering, Poznan University of Technology, 24 Jana Pawla II, 60-965 Poznan, Poland

关键词: Keywords: optimization;    fluid-structure interaction;    coupling techniques;    biomimetics;   

DOI  :  10.1515/bpasts-2017-0080

学科分类：工程和技术（综合）

来源: Polska Akademia Nauk * Centrum Upowszechniania Nauki / Polish Academy of Sciences, Center for the Advancement of Science

【 摘 要 】

This paper presents a new biomimetic approach to the structural design. For the purpose of aircraft wing design the numerical environment combining simultaneous structural size, shape, and topology optimization based on aeroelastic analysis was developed. For the design of aircraft elements the optimization process must be treated as a multi-load case task, because during the fluid structure interaction analysis each step represents a different structural load case. Also, considering different angles of attack, during the CFD computation each result is considered. The method-specific features (such as domain independence, functional configurations during the process of optimization, and multiple load case solution implemented in the optimization scenario) enable the optimal structural form. To illustrate the algorithm functionality, the problem of determining the optimal internal wing structure was presented. The optimal internal wing structure resulting from aeroelastic computation with different angles of attack has been presented.

【 授权许可】

Unknown