Development of an automated missile design and analysis tool integrated with structured mesh generator Tam düzenli ağ üreteciyle entegre edilmiş otomatik mühimmat tasarım ve analiz yazılımı geliştirilmesi


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Köseömür O. Z., BARAN Ö. U.

Journal of the Faculty of Engineering and Architecture of Gazi University, cilt.38, sa.4, ss.1995-2008, 2023 (SCI-Expanded) identifier identifier identifier

  • Yayın Türü: Makale / Tam Makale
  • Cilt numarası: 38 Sayı: 4
  • Basım Tarihi: 2023
  • Doi Numarası: 10.17341/gazimmfd.719712
  • Dergi Adı: Journal of the Faculty of Engineering and Architecture of Gazi University
  • Derginin Tarandığı İndeksler: Science Citation Index Expanded (SCI-EXPANDED), Scopus, Academic Search Premier, Art Source, Compendex, TR DİZİN (ULAKBİM)
  • Sayfa Sayıları: ss.1995-2008
  • Anahtar Kelimeler: Missile design, structure mesh generator, Overset solver, CFD
  • Orta Doğu Teknik Üniversitesi Adresli: Evet

Özet

Missile aerodynamic design studies require flight control of an aircraft that passes through diverse flight regimes with extreme maneuvering requirements, using a minimal control surface set. These challenging goals are achieved typically using a simplified pre-design tool among thousands of body-fin alternatives. Alternative geometries found at this stage are then transferred to the computational domains, and CFD analyses are conducted to ensure aerodynamic performance. However, this new stage involves a costly and time-consuming preprocessing workload. For this reason, the number of missile geometries transferred from the pre-design stage is very limited. Considering that pre-design tools cannot provide sufficiently precise results, it is seen that this transfer mechanism should be replaced with a new method that is less costly than traditional workflow but more precise than pre-design tools. This study presents a new software tool that uses Missile DATCOM design terminology to generate solution domain and computational mesh automatically. This technology generates a remarkably high-quality structured mesh around the missile geometry. Fin control angles can be applied, and CFD analyses are performed at desired flight conditions. CFD analyses are performed using an in-house compressible CFD tool, and a good match with the experimental results is observed.