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Communication Dans Un Congrès Année : 2017

Static and Dynamic Aeroelastic Scaling of the CRM Wing via Multidisciplinary Optimization

J. Mas Colomer
  • Fonction : Auteur
N. Bartoli
  • Fonction : Auteur
T. Lefebvre
  • Fonction : Auteur
S. Dubreil
  • Fonction : Auteur
P. Schmollgruber
  • Fonction : Auteur
J.R.R. Martins
  • Fonction : Auteur
Joseph Morlier

Résumé

Novel and disruptive aircraft configurations such as the blended wing-body, the truss-braced wing or the joined-wing aircraft aim to improve the performance of the classical wingbody aircraft. However, there are few to no data of previous similar aircraft to use for the design of these new concepts. For this reason, the use of aeroelastically similar flight demonstrators arises as a means to assess the flight qualities of these new concepts. Since flight demonstrators cannot often be a scaled down copy in all the aspects (e.g., the internal structure architecture), an optimization approach is needed to find the design that best fits the desired response. In this paper, we present a multidisciplinary optimization approach to design a wing that matches the aeroelastic response of the NASA Common Research Model (CRM). This response includes both the static deformed shape, and the scaled flutter modes, speeds and frequencies. In previous works, we successfully tested both the aeroelastic coupling and the dynamic similarity optimization by using test cases on the literature. All multidisciplinary analysis and optimizations were implemented using OpenMDAO framework. We used a global optimizer with surrogate models and mixture of experts. For the static aeroelastic part of the problem, we establish a coupling between a panel code and a linear finite element solver by using a GaussSeidel iterative method. The optimizer tries to minimize the difference between the nodal displacements of the scaled model and the scaled response of the reference aircraft. For the dynamic aeroelastic similarity, we first use the traditional approach where aerodynamic similarity is assumed and the problem can be treated as a structural modal optimization. For the optimization, we maximize the sum of the Modal Assurance Criterion (MAC) between the reference and current design modes once they have been paired according to their shape. The MAC value is also used to pair the modes.
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Dates et versions

hal-02047625 , version 1 (25-02-2019)

Identifiants

  • HAL Id : hal-02047625 , version 1

Citer

J. Mas Colomer, N. Bartoli, T. Lefebvre, S. Dubreil, P. Schmollgruber, et al.. Static and Dynamic Aeroelastic Scaling of the CRM Wing via Multidisciplinary Optimization. WCSMO12 12th World Congress of Structural and Multidisciplinary Optimisation 5 - 9 June 2017, Braunschweig, Germany, 2017, Braunschweig, Germany. ⟨hal-02047625⟩
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