Aerodynamic-structural missile fin optimization

Nenad Vidanović

doi:10.1016/j.ast.2017.02.010

Aerodynamic-structural missile fin optimization

2017-06-01

37

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AI

DOI：10.1016/j.ast.2017.02.010

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The aim of the paper is to establish and demonstrate the significant capacity and performances of a well predictive numerical environment, developed for multidisciplinary design optimization (MDO) purposes, which presents one more contribution in cases of fluid-structure interaction (FSI) numerical modeling. Numerical modeling of fluid-structure interaction was conducted through closely coupled aerodynamic and structural computational domains, with very good overall computational reliability and accuracy. Various available experimental results, which were obtained mostly for calibration purposes, have been used for computational fluid dynamics (CFD) and computational structural mechanics (CSM) validation and verification, in order to assure that numerical optimization could be carried out with acceptable accuracy. The numerical optimization procedure was applied on the short range ballistic missile fin configuration, which was developed for scientific and internal experimental, testing and calibration purposes in Military Technical Institute (VTI) in Belgrade. The proposed monolithic, multimodular and on commercial code based numerical environment, with adopted multipoint regimes and multicriteria settings was used for aerodynamic-structural optimization. The multidiscipline aerodynamic shape optimization, with respect to predefined objectives and constrains, was carried out in order to achieve global improvement of initial aerodynamic-structural responses of the mentioned configuration. The multidisciplinary feasible method proposed in this paper, is a single level method driven by an embedded surrogate-based evolutionary optimizer. The developed algorithm enabled an increased number of feasible optimal geometries of fin, while its special feature was the overall improvement of the missile initial geometry, with decreased costs of experimental and numerical resources. A special challenge of this research was to overcome scaling between available the wind tunnel missile model geometry, used for aerodynamic experiments, and the real fin geometry model, used for static structural experiments. (C) 2017 Elsevier Masson SAS. All rights reserved.

Keyword:

Fluid-structure interaction

Multidisciplinary design optimization

Genetic algorithm

Surrogate-based modeling

Experimental aerodynamics

Experimental strength

Aerodynamic-structural missile fin optimization

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