Optimization of Low-Altitude UAV Wing Design Using Comparative Statistical Analysis Method

Öz

Today, unmanned aerial vehicles (UAV) are widely used across various fields, including civil, military, and social activities. Fixed-wing UAV operating at low altitudes typically have a wingspan ranging from 2 to 4 meters and can sustain flight for up to three hours. Their wing structure generally consists of three main components: a central wing that bears the primary structural load, and left and right side wings that are critical for determining flight endurance and speed. The lengths of these components vary, with the side wings designed at an angle to reduce wind resistance and enhance flight speed. In this study, three main parameter levels were identified for an average low-altitude drone, and the optimal dimensions were evaluated using RSM (Response Surface Methodology), the Taguchi method, FEM (Finite Element Method), and Analysis of Variance (ANOVA) analyses. The optimal design was achieved with a central wing length of 400 mm, side wing lengths of 700 mm, and a side wing angle of approximately 8°. Analysis results showed a maximum lift force (FZ) of 253 N, a minimum drag force of 10.2 N, a maximum lift coefficient (CL) of 0.66, and a lift-to-drag (CL/CD ) ratio of 17.6. Based on these findings, composite molds were manufactured for the aircraft, and a testing device was developed to measure speed during flight trials. Under 10 m/s wind conditions, the maximum speed recorded for this optimized geometry was 183 km/h.

Anahtar Kelimeler

• Wing Design
• Low-Altitude UAV
• Unmanned Aerial Vehicle Optimization FEM
• Aerodynamics

Karşılaştırmalı İstatistiksel Analiz Yöntemi Kullanılarak Alçak İrtifa İHA Kanat Tasarımının Optimizasyonu

Öz

Günümüzde insansız hava araçları (İHA) sivil, askeri ve sosyal faaliyetler de dahil olmak üzere çeşitli alanlarda yaygın olarak kullanılmaktadır. Alçak irtifalarda çalışan sabit kanatlı İHA'lar tipik olarak 2 ila 4 metre arasında değişen kanat açıklığına sahiptir ve üç saate kadar uçuşlarını sürdürebilirler. Kanat yapıları genellikle üç ana bileşenden oluşur: birincil yapısal yükü taşıyan merkezi bir kanat ve uçuş dayanıklılığını ve hızını belirlemek için kritik olan sol ve sağ yan kanatlar. Bu bileşenlerin uzunlukları değişmekte olup, yan kanatlar rüzgâr direncini azaltmak ve uçuş hızını artırmak için açılı olarak tasarlanmıştır. Bu çalışmada, ortalama bir alçak irtifa drone'u için üç ana parametre seviyesi belirlenmiş ve optimum boyutlar RSM (Yanıt Yüzeyi Metodolojisi), Taguchi yöntemi, FEM (Sonlu Elemanlar Yöntemi) ve Varyans Analizi (ANOVA) analizleri kullanılarak değerlendirilmiştir. Optimum tasarım 400 mm merkezi kanat uzunluğu, 700 mm yan kanat uzunluğu ve yaklaşık 8° yan kanat açısı ile elde edilmiştir. Analiz sonuçları 253 N maksimum kaldırma kuvveti (FZ), 10.2 N minimum sürükleme kuvveti, 0.66 maksimum kaldırma katsayısı (CL) ve 17.6 kaldırma-sürükleme (CL/CD ) oranı göstermiştir. Bu bulgulara dayanarak, hava aracı için kompozit kalıplar üretildi ve uçuş denemeleri sırasında hızı ölçmek için bir test cihazı geliştirildi. 10 m/s rüzgar koşulları altında, bu optimize edilmiş geometri için kaydedilen maksimum hız 183 km/s olmuştur.

Anahtar Kelimeler

• Kanat Tasarımı
• Alçak İrtifa İHA
• İnsansız Hava Aracı Optimizasyonu FEM
• Aerodinamik

Kaynakça

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