Hasan İBAÇOĞLU, Aytaç ARIKOĞLU

3112

Gelişmiş Helikopter Rotor Palaları İçin Çok Disiplinli Kavramsal TasarımMetodu ve Tasarım Aracı

Bu çalışmada, helikopter kavramsal tasarım, boyutlandırma ve değerlendirme aşamalarında kullanıma uygun, çok disiplinli rotor palası tasarım yaklaşımı anlatılmıştır. Pala boyunca lineer ve non-lineer dağılım fonksiyonları olarak tarif edilmiş veter, kalınlık oranı, kamburluk oranı, ve burulma parametreleri ile pala dış yüzeyi ve yapısal geometri temsil edilmektedir. Kaplama ve spar için katman sayılarının dağılımı da çalışmada izah edilen modelde gösterilmiştir. Düşük seviyede fakat yeter çözünürlükte analiz methodları seçilerek toplam çözüm süresi azaltılmıştır. ROTAP adlı, BEMT metdou ile çalışan ve yazar tarafınfa geliştirilmiş helikopter boyutlandırma kodu, performans analizleri ve boyutlandırmada kullanılmıştır. Airfoillerin aerodinamik karakteristikleri ise, literatürde iyi bilinen bir panel kodu olan Xfoil yardımıyla hesaplanmıştır. Yapısal analizlerde bir boyutlu sonlu elemanlar yaklaşımı kullanılmışıtır. Kiriş kesit özellikleri VABS, yükler altında ki deplasmanlar ise GEBT yardımı ile hesaplanmıştır. Tüm bu yazılımlar modifiye edilerek geliştirilen algoritma içerisine gömülerek kullanıcı dostu bir arayüzü olan tek bir kod altında birleştirilmiştir. Geliştirilen algoritma ve tasarım aracı, rotor tasarımı kavramsal tasarım aşamasında palanın performans ve yapısal dayanım analizlerinde kullanılabilir.

Multidisciplinary Conceptual Design Methodology and Design Tool for Rotor Blades of Advanced Helicopters

A multidisciplinary rotor blade design approach, which is suitable for conceptual design, sizing and evaluation of helicopters is presented. Blade outer surface and structural geometry is represented by a geometrical model in which chord, thickness ratio, camber ratio and twist distributions along the blade radial stations can be defined as linear or nonlinear functions. Distribution of the number of laminas for both skin and spar were also defined in the presented model parametrically. Low level fidelity analysis methods were chosen to reduce the computing time. Performance analysis and sizing of the vehicle are performed by an in-house developed code named as ROTAP based on BEMT. Airfoil aerodynamic characteristics are calculated by Xfoil, a well-known panel method software. Structural analyses are performed by 1D finite element method approach. Cross-sectional properties of the composite beam are calculated by VABS software and displacements under the loads are calculated by the GEBT. All these programs are modified and embedded into the developed code and a single program with user friendly interface emerged. Developed algorithm and tool can be used for performance and structural strength calculations during the rotor design optimization studies at the conceptual design stage.
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Havacılık ve Uzay Teknolojileri Dergisi-Cover
  • ISSN: 1304-0448
  • Yayın Aralığı: Yılda 2 Sayı
  • Başlangıç: 2003
  • Yayıncı: Dr. Öğr. Üyesi Fatma Kutlu Gündoğdu
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