Design and Optimization Method for Scaled Equivalent Model of T-Tail Configuration Structural Dynamics Simulating Fuselage Stiffness
Guardat en:
| Publicat a: | Aerospace vol. 12, no. 12 (2025), p. 1063-1088 |
|---|---|
| Autor principal: | |
| Altres autors: | , , , |
| Publicat: |
MDPI AG
|
| Matèries: | |
| Accés en línia: | Citation/Abstract Full Text + Graphics Full Text - PDF |
| Etiquetes: |
Sense etiquetes, Sigues el primer a etiquetar aquest registre!
|
MARC
| LEADER | 00000nab a2200000uu 4500 | ||
|---|---|---|---|
| 001 | 3286238352 | ||
| 003 | UK-CbPIL | ||
| 022 | |a 2226-4310 | ||
| 024 | 7 | |a 10.3390/aerospace12121063 |2 doi | |
| 035 | |a 3286238352 | ||
| 045 | 2 | |b d20250101 |b d20251231 | |
| 084 | |a 231330 |2 nlm | ||
| 100 | 1 | |a Chen, Zheng |u School of Mechanical Engineering, Dalian University of Technology, Dalian 116023, China | |
| 245 | 1 | |a Design and Optimization Method for Scaled Equivalent Model of T-Tail Configuration Structural Dynamics Simulating Fuselage Stiffness | |
| 260 | |b MDPI AG |c 2025 | ||
| 513 | |a Journal Article | ||
| 520 | 3 | |a The T-tail configuration, while offering advantages for large transport aircraft, is susceptible to peculiar aerodynamic phenomena such as deep stall and flutter, necessitating high-fidelity dynamic scaling for wind tunnel testing. In order to address the issue of similarity in the dynamic characteristics of scaled T-tail models, we propose a comprehensive optimization design method for dynamic scaled equivalent models of T-tail structures with rear fuselages. The development of an elastic-scaled model is accomplished through the integration of the least squares method with a genetic sensitivity hybrid algorithm. In this framework, the objective function is defined as minimizing a weighted sum of the frequency errors and the modal shape discrepancies (<inline-formula>1−</inline-formula> Modal Assurance Criterion) for the first five modes, subject to lower and upper bound constraints on the design variables (e.g., beam cross-sectional dimensions). The findings indicate that the application of finite element modelling in conjunction with multi-objective optimization results in the scaled model that closely aligns with the dynamic characteristics of the actual aircraft structure. Specifically, the frequency error of the optimized model is maintained below 2%, while the modal confidence level exceeds 95%. A ground vibration test (GVT) was conducted on a fabricated scaled model, with all frequency errors below 3%, successfully validating the optimization approach. This GVT-validated high-fidelity model establishes a reliable foundation for subsequent wind tunnel tests, such as flutter and buffet experiments, the results of which are vital for validating the full-scale aircraft’s aeroelastic model and informing critical flight safety assessments. The T-tail elastic model design methodology presented in this study serves as a valuable reference for the analysis of T-tail characteristics and the design of wind tunnel models. Furthermore, it provides insights applicable to multidisciplinary optimisation and the design of wind tunnel models for other similar elastic scaled-down configurations. | |
| 653 | |a Finite element method | ||
| 653 | |a Aircraft aerodynamics | ||
| 653 | |a Software | ||
| 653 | |a Fuselages | ||
| 653 | |a Optimization techniques | ||
| 653 | |a Wind tunnel testing | ||
| 653 | |a Equivalence | ||
| 653 | |a Transport aircraft | ||
| 653 | |a Least squares method | ||
| 653 | |a Flutter | ||
| 653 | |a Wind tunnels | ||
| 653 | |a Multiple objective analysis | ||
| 653 | |a Dynamic characteristics | ||
| 653 | |a Modal assurance criterion | ||
| 653 | |a Design | ||
| 653 | |a Airframes | ||
| 653 | |a Aircraft | ||
| 653 | |a Flight safety | ||
| 653 | |a Simulation | ||
| 653 | |a Aircraft structures | ||
| 653 | |a Upper bounds | ||
| 653 | |a Confidence intervals | ||
| 653 | |a Aerodynamics | ||
| 653 | |a Objective function | ||
| 653 | |a Wind tunnel models | ||
| 653 | |a Mathematical models | ||
| 653 | |a Errors | ||
| 653 | |a Algorithms | ||
| 653 | |a Design optimization | ||
| 653 | |a Vibration tests | ||
| 700 | 1 | |a Ai Xinyu |u School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116023, China; axy@dlut.edu.cn (X.A.); | |
| 700 | 1 | |a Feng Weizhe |u School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116023, China; axy@dlut.edu.cn (X.A.); | |
| 700 | 1 | |a Yang, Rui |u School of Mechanical Engineering, Dalian University of Technology, Dalian 116023, China | |
| 700 | 1 | |a Qian, Wei |u School of Mechanics and Aerospace Engineering, Dalian University of Technology, Dalian 116023, China; axy@dlut.edu.cn (X.A.); | |
| 773 | 0 | |t Aerospace |g vol. 12, no. 12 (2025), p. 1063-1088 | |
| 786 | 0 | |d ProQuest |t Advanced Technologies & Aerospace Database | |
| 856 | 4 | 1 | |3 Citation/Abstract |u https://www.proquest.com/docview/3286238352/abstract/embedded/6A8EOT78XXH2IG52?source=fedsrch |
| 856 | 4 | 0 | |3 Full Text + Graphics |u https://www.proquest.com/docview/3286238352/fulltextwithgraphics/embedded/6A8EOT78XXH2IG52?source=fedsrch |
| 856 | 4 | 0 | |3 Full Text - PDF |u https://www.proquest.com/docview/3286238352/fulltextPDF/embedded/6A8EOT78XXH2IG52?source=fedsrch |