期刊
INTERNATIONAL JOURNAL OF AERONAUTICAL AND SPACE SCIENCES
卷 -, 期 -, 页码 -出版社
SPRINGER
DOI: 10.1007/s42405-023-00603-6
关键词
Composites; Optimization; Aeroelastic analysis; Structural analysis; Numerical modeling
The paper presents a systematic numerical design for optimizing composite wings under aerodynamic loading and evaluates their aeroelastic and structural performance. By utilizing the anisotropic features of composite materials, a method called aeroelastic tailoring is proposed. The methodology combines three different analysis tools: a commercial FE software, an in-house reduced order aeroelastic framework, and in-house linkage-learning genetic algorithms for optimization. The proposed methodology can be effectively applied to any arbitrary air vehicle's composite wing by changing input data.
The paper aims to develop a systematic numerical design for composite wings optimization subject to aerodynamic loading and to assess the aeroelastic and structural performance of the optimized composite wing. Aeroelastic tailoring is a powerful method for utilizing the anisotropic features of composite materials used in lightweight aerospace structures. The present proposed methodology combines three different analysis tools: a commercial FE software commonly used in industry, an in-house reduced order aeroelastic framework for aeroelastic analyses with tailoring capabilities, LLGA, in-house linkage-learning genetic algorithms for optimization of stacking sequences. As a multidisciplinary problem where structural and aeroelastic behaviors are interacted, developed multi-level optimization scenario in this research converges to the optimal design in a very short time. The proposed methodology implemented as a computer code can effectively be applied to any arbitrary air vehicle's composite wing by changing input data.
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