This paper describes a wing mass estimation approach based on a bi-level optimization process and an automated CAD-CAE integration framework. The design framework goes through parametric CAD model generation, aerodynamic load calculation, finite element modeling, structural analysis and sizing. In the lower-level task, the wing box is sized to optimize the structural element thicknesses under a maximum stress constraint for a fixed planform configuration. The upper-level optimization determines the optimal planform shape to minimize the wing mass while maintaining a good lift-to-drag ratio. The process chain involves SIEMENS NX for geometric modeling, VORLAX VLM for aerodynamic calculations and MSC. NASTRAN for FE analysis and sizing. The outer optimization is performed by the multi-objective genetic algorithm on a radial basis function surrogate model.
Structural wing sizing and planform shape optimization using multidisciplinary CAD-CAE integration process
01.07.2017
491112 byte
Aufsatz (Konferenz)
Elektronische Ressource
Englisch
Subsonic Wing Planform Design Using Multidisciplinary Optimization
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