Multi-disciplinary Shape Optimization of Missile Fin Configuration Subject to Aerodynamic Heating

Abstract

The main goal of this paper is to expand previously conducted study and consequently to upgrade the proposed multimodular numerical framework developed for fluid–structure interaction simulation (FSI) and multidisciplinary design optimization (MDO) purposes, in a manner that thermal–structure interaction is observed and implemented into the established numerical framework. The upgraded and considerably improved algorithm was used for MDO of the short-range ballistic missile (SRBM) model. Because of its high-speed regimes, this aircraft model was selected for the purpose of numerical modeling and optimization of aerodynamically heated structure. The present study is concerned with a broader observation of critical multipoint flight conditions and represents a more realistic scenario, which indicates this study as one contribution more in a scope of fluid–thermal–structure interaction (FTSI) numerical modeling and optimization. With respect to predefined objectives and constraints, multidisciplinary shape optimization of the fin structure resulted in overall improvement of the missile initial performances. Also, aerothermally induced critical responses of the fin structure were prevented. Numerical modeling of FSI/FTSI and MDO within an industry-accepted design tool resulted in powerful monolithic environment, which, with adopted multipoint regimes and multicriteria settings, was used for aerodynamic–thermal/structural optimization. The obtained results were compared with the results from the previous study conducted without thermal effects.