CFD-FEA Entegrasyonu ile Subsonik Füze Kanatçıklarında Alüminyum 5754 ve Karbon Fiber Yapısal Tepkilerinin Kıyaslanması

Abstract

Bu çalışmada, 1 Mach altı seyir hızlarında kullanılan füze kanatçık sistemleri için 5754 alüminyum alaşımı ve epoksi matrisli yüksek modüllü karbon fiber takviyeli polimer (CFRP) malzemeler yapısal ve aerodinamik açıdan karşılaştırılmıştır. Öncelikle CFD analizleri ile kanatçık yüzeylerindeki basınç dağılımları belirlenmiş, ardından bu yükler sonlu elemanlar analizlerinde uygulanarak gerilme, deformasyon, güvenlik katsayısı ve titreşim özellikleri hesaplanmıştır. Analizler, aerodinamik yüklerin özellikle kanatçık kök ve ön kenar bölgelerinde yoğunlaştığını göstermiştir. Karbon fiber, düşük yoğunluğu ve yüksek elastisite modülü sayesinde daha düşük deformasyon ve yüksek rijitlik sağlamıştır. Alüminyum ise daha yüksek sönüm oranı ile belirli titreşim senaryolarında avantaj sunmuş, ayrıca üretim, bakım ve onarım kolaylığı açısından öne çıkmıştır. Sonuç olarak, hafiflik ve yüksek rijitliğin öncelikli olduğu durumlarda karbon fiber, maliyet ve bakım kolaylığının öncelikli olduğu durumlarda ise alüminyum tercih edilebilecek malzemeler olarak değerlendirilmiştir.

Keywords

• Füze
• Kanatçık
• Alüminyum 5754
• Karbon Fiber
• Kompozit

Comparison of Structural Responses of Aluminum 5754 and Carbon Fiber in Subsonic Missile Wings Using CFD-FEA Integration

Abstract

This study aims to comparatively analyze the structural performance of metallic (Aluminum 5754) and composite (Epoxy/CFRP) materials used for control flaps in missiles with subsonic flight speeds below Mach 1. Based on the fundamental problem of weight and strength optimization in aerospace structures, a unidirectional analysis method simulating fluid-structure interaction was used. As a method, aerodynamic pressure loads obtained from CFD analyses were integrated into a finite element model (FEA) to examine the stress, deformation, and vibration characteristics of the materials. Numerical results confirmed that aerodynamic loads reached their maximum level at the root and leading edge of the winglets. It was found that carbon fiber reinforced structures offer a distinct advantage over aluminum in limiting deformation and increasing rigidity due to their high specific strength properties. However, it was observed that aluminum material remains a valid alternative due to its damping properties and cost advantages in manufacturing/maintenance processes. As a result of the study, material selection criteria were established based on the “performance/cost” balance required by the mission profile.

Keywords

• Missile
• Winglet
• Aluminum 5754
• Carbon Fiber
• Composite

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