Impacts of Tapered Wingtip on Lateral-Directional Stability Coefficients of a Morphing Fixed-wing UAV

Tuğrul Oktay; Yüksel Eraslan

Makale detayları

Impacts of Tapered Wingtip on Lateral-Directional Stability Coefficients of a Morphing Fixed-wing UAV

Yazarlar:

Tuğrul Oktay | Yüksel Eraslan

Yayıncı:

Giresun University

Ana Başlıklar:

Malzeme Mühendisliği (Diğer)

Dergi:

Karadeniz Fen Bilimleri Dergisi Vol.13 Issue 4, pp.1540-1551

Belge Tipi:

Makale

Yayın Tarihi:

12/2023

Belge Dili:

İngilizce

Document ID (Org No.):

2001305313

pISSN:

2564-7377

Anahtar kelimeler:

Özet:

 Recent developments in unmanned aerial vehicle UAV technologies have shown the possibility of morphing applications to provide improvement in various performance metrics in the desired manner. In rotary-wing UAVs, applications mainly focused on propeller blades and rotor arms, while efforts on fixed-wing UAVs mainly concentrated on the main wing and tail geometries. Although every morphing design has its own advantages and disadvantages, all of the applications have similar common purposes to have improved aerodynamics, flight performance, control responses, or a combination of such objectives. In that context, new morphing design attempts require a precise investigation of their pros and cons. Thus, in this study, a new morphing scenario of tapering morphing wingtip is applied to ZANKA-I fixed-wing UAV and investigated in terms of lateral-directional stability considerations. The lateral dynamic model of the aircraft is constituted and necessary aerodynamic, geometric, and inertial assessments are numerically and analytically performed. The lateral-directional stability coefficients are discussed and an improvement in lateral stability is obtained, while directional stability is found to be affected negatively by the morphing application.

 Recent developments in unmanned aerial vehicle UAV technologies have shown the possibility of morphing applications to provide improvement in various performance metrics in the desired manner. In rotary-wing UAVs, applications mainly focused on propeller blades and rotor arms, while efforts on fixed-wing UAVs mainly concentrated on the main wing and tail geometries. Although every morphing design has its own advantages and disadvantages, all of the applications have similar common purposes to have improved aerodynamics, flight performance, control responses, or a combination of such objectives. In that context, new morphing design attempts require a precise investigation of their pros and cons. Thus, in this study, a new morphing scenario of tapering morphing wingtip is applied to ZANKA-I fixed-wing UAV and investigated in terms of lateral-directional stability considerations. The lateral dynamic model of the aircraft is constituted and necessary aerodynamic, geometric, and inertial assessments are numerically and analytically performed. The lateral-directional stability coefficients are discussed and an improvement in lateral stability is obtained, while directional stability is found to be affected negatively by the morphing application.

 Recent developments in unmanned aerial vehicle UAV technologies have shown the possibility of morphing applications to provide improvement in various performance metrics in the desired manner. In rotary-wing UAVs, applications mainly focused on propeller blades and rotor arms, while efforts on fixed-wing UAVs mainly concentrated on the main wing and tail geometries. Although every morphing design has its own advantages and disadvantages, all of the applications have similar common purposes to have improved aerodynamics, flight performance, control responses, or a combination of such objectives. In that context, new morphing design attempts require a precise investigation of their pros and cons. Thus, in this study, a new morphing scenario of tapering morphing wingtip is applied to ZANKA-I fixed-wing UAV and investigated in terms of lateral-directional stability considerations. The lateral dynamic model of the aircraft is constituted and necessary aerodynamic, geometric, and inertial assessments are numerically and analytically performed. The lateral-directional stability coefficients are discussed and an improvement in lateral stability is obtained, while directional stability is found to be affected negatively by the morphing application.

 Son dönemlerde insansız hava aracı İHA teknolojilerindeki gelişim, başkalaşım uygulamalarının çeşitli hava aracı performans parametrelerinde iyileştirme elde edebilmek adına potansiyelini ortaya koymaktadır. Döner kanatlı İHAlarda uygulamalar genellikle pervane pal geometrisi ve rotor kolları üzerine odaklanmışken, sabit kanatlı İHAlarda ise girişimler özellikle kanat ve kuyruk geometrilerinde yoğunlaşmıştır. Her başkalaşım tasarımının kendine özgü avantaj ve dezavantajları olduğu bilinse de tüm uygulamaların aerodinamik, uçuş performansı, kontrol tutumu veya bunların bir kombinasyonu olan benzer ortak amaçlar çevresinde buluştuğu görülmektedir. Bu çerçevede, yeni başkalaşım tasarımı girişimlerinin özenli şekilde avantaj ve dezavantajlarının değerlendirilmesi gerekmektedir. Buradan hareketle, bu çalışmada, yeni bir başkalaşım senaryosu olarak ZANKA-I İHA kanat ucu konikleşme kabiliyetine sahip şekilde yeniden tasarlanmış ve yanal-yön kararlılığı açısından değerlendirilmiştir. Hava aracının yanal dinamik modeli oluşturulmuş ve bu süreçte ihtiyaç duyulan aerodinamik, geometrik ve ataletsel değişkenler analitik ve sayısal yöntemlerle elde edilmiştir. Yanal-yön kararlılığı katsayıları değerlendirildiğinde ise uygulamanın yanal kararlılıkta bir gelişme sağladığı görülmüş, fakat yön kararlılığında olumsuz etkilerin baskın olduğu görülmüştür.

Makale detayları

Impacts of Tapered Wingtip on Lateral-Directional Stability Coefficients of a Morphing Fixed-wing UAV

Yazarlar:

Tuğrul Oktay | Yüksel Eraslan

Yayıncı:

Giresun University

Ana Başlıklar:

Malzeme Mühendisliği (Diğer)

Dergi:

Karadeniz Fen Bilimleri Dergisi Vol.13 Issue 4, pp.1540-1551

Belge Tipi:

Makale

Yayın Tarihi:

12/2023

Belge Dili:

İngilizce

Document ID (Org No.):

2001305313

pISSN:

2564-7377

Morphing

Unmanned aerial vehicle

Lateral stability

Directional stabilityBaşkalaşım

İnsansız hava aracı

Yanal kararlılık

Yön kararlılığı

Sayı

Makale detayları

Yazarlar: Tuğrul Oktay | Yüksel Eraslan

Yayıncı: Giresun University

Ana Başlıklar: Malzeme Mühendisliği (Diğer)

Dergi: Karadeniz Fen Bilimleri Dergisi Vol.13 Issue 4, pp.1540-1551

Belge Tipi: Makale

Yayın Tarihi: 12/2023

Belge Dili: İngilizce

Document ID (Org No.): 2001305313

pISSN: 2564-7377

Sayı

Yazarlar:

Tuğrul Oktay | Yüksel Eraslan

Yayıncı:

Giresun University

Ana Başlıklar:

Malzeme Mühendisliği (Diğer)

Dergi:

Karadeniz Fen Bilimleri Dergisi Vol.13 Issue 4, pp.1540-1551

Belge Tipi:

Makale

Yayın Tarihi:

12/2023

Belge Dili:

İngilizce

Document ID (Org No.):

2001305313

pISSN:

2564-7377