SpaRibs Geometry Parameterization for Wings with Multiple Sections using Single Design Space
| Autor: | Myles L. Baker, Shuvodeep De, Davide Locatelli, Rakesh K. Kapania, Mohamed Jrad, Chan-gi Pak |
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| Rok vydání: | 2017 |
| Předmět: |
Airfoil
020301 aerospace & aeronautics Engineering Curvilinear coordinates Wing business.industry Angle of attack Multidisciplinary design optimization Geometry 02 engineering and technology Structural engineering Finite element method Discontinuity (linguistics) 020303 mechanical engineering & transports 0203 mechanical engineering Flutter business |
| Zdroj: | 58th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference. |
| DOI: | 10.2514/6.2017-0570 |
| Popis: | The SpaRibs topology of an aircraft wing has a significant effect on its structural behavior and stability as well as the flutter performance. The development of additive manufacturing techniques like Electron Beam Free Form Fabrication (EBF3) has made it feasible to manufacture aircraft wings with curvilinear spars, ribs (SpaRibs) and stiffeners. In this article a new global-local optimization framework for wing with multiple sections using curvilinear SpaRibs is described. A single design space is used to parameterize the SpaRibs geometry. This method has been implemented using MSC-PATRAN to create a broad range of SpaRibs topologies using limited number of parameters. It ensures C0 and C1 continuities in SpaRibs geometry at the junction of two wing sections with airfoil thickness gradient discontinuity as well as mesh continuity between all structural components. This method is advantageous in complex multi-disciplinary optimization due to its potential to reduce the number of design variables. For the global-local optimization the local panels are generated by an algorithm which is totally based on a set algebra on the connectivity matrix data. The great advantage of this method is that it is completely independent of the coordinates of the nodes of the finite element model. It is also independent of the order in which the elements are distributed in the FEM. The code is verified by optimizing of the CRM Baseline model at trim condition at Mach number equal to 0.85 for five different angle of attack (-2deg, 0deg,2deg,4deg and 6deg). The final weight of the wing is 19,090.61 lb. This value is comparable to that obtained by Qiang et al. 6 (19,269 lb). |
| Databáze: | OpenAIRE |
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