Farklı tip quadcopter kanadının uçuş doğrultu kararlılığına etkilerinin deneysel ve sayısal analizi
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Tarih
2023-01-12
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Yayıncı
Batman Üniversitesi Lisansüstü Eğitim Enstitüsü
Erişim Hakkı
info:eu-repo/semantics/openAccess
Özet
İnsansız hava araçları (İHA) günümüzde savunma, eğlence, tarım, harita ve taşımacılık gibi birçok alanda kullanılmaktadır. Hava aracı ile birlikte bir pilota gerek olmaması ve otonom sürüşe imkân vermesi ile bu araçların kullanımı gün geçtikçe diğer sektörlerde de görülmeye başlamıştır. Buna ek olarak teknolojinin gelişmesi ile elektronik parça ve sensörlerin ucuzlaması, bu sektörün gelişmesine olanak vermiştir. İHA’ların en popüleri olan Quadcopter, dört kanada sahiptir. Bu tez için otonom uçuş özelliğine sahip bir Quadcopter oluşturulmuştur. Çalışmada Pixhawk 4 uçuş kontrol kartı, otonom uçuş özelliğinden dolayı tercih edilmiştir. Otonom uçuş, Pixhawk kontrol kartını destekleyen Mission Planer yazılımı ile planlanarak gerçekleştirilmiştir. Kanat doğrultu kararlılığını belirlemek için 4 farklı pervane tasarımı yapılmıştır. Tasarlanan pervaneler arasından uçuş süresi ve doğrultu kararlılığı açısından en verimli Quadcopter pervane profili araştırılmıştır. Literatür araştırmaları sonucunda düşük Reynolds sayısında (Re<100.000) iyi performans gösterdiği belirtilen DAE51, MH42, NACA4412 ve NLF0115 kanat profilleri, bu araştırma için seçilmiştir. Tasarlanan bu pervanelerin etkilerini ortaya koymak için Hesaplamalı Akışkanlar Dinamiği (HAD) ve deneysel analiz yapılmıştır. Pervane hesaplamalarının doğruluğunu tespit etmek için ANSYS Fluent simülasyon analizi yapılmıştır. ANSYS Fluent için doğrulanabilir bir yöntem ortaya koymak için de literatürde kesit ölçüleri ve aerodinamik performansı bulunan APC 10x7 pervane ile doğrulama yapılmıştır. Analitik hesaplama ile elde edilen itki katsayısı HAD analizi ile karşılaştırıldığında, DAE51 tasarım pervanesi için %4,41, MH42 için %4,91, NACA0115 için %5,80 ve NLF0115 için %5,94 daha düşük oluşmuştur. Quadcopter için gerekli itki kuvvetinin meydana geleceği, sonuçlar ile ortaya konduktan sonra üç boyutlu yazıcı ile baskı yapılmıştır. Deneysel analiz, dış ortamda gerçekleştirilmiştir. Dış ortam testlerinde, pervanenin rüzgâr etkileri göz önünde bulundurulmuştur. DAE51, MH42, NACA4412 ve NLF0115 profillerinden tasarlanan pervaneler, Quadcopter’ın orijinal pervanesinin performansı ile karşılaştırılmıştır. Yapılan deneyler sonucunda istenilen ve oluşan yunuslama, yuvarlanma, sapma açıları, yükseklik ve titreşim değerlerinde önemli farklılıklar ortaya çıkmadığı görülmüştür. Yapılan ilk ve ikinci deneyde sırasıyla DAE51 için 0,072 m ve 0,05 m, MH42 için 0,019 m ve 0,13 m, NACA4412 için 0,031 m ve 0,03 m ve NLF0115 için 0,022 m ve 0,028 m ortalama sapma miktarı meydana gelmiştir. Pervaneler, menzil ve doğrultu kararlılığı parametreleri ile değerlendirildiğinde en iyi pervane performansına NACA4412 sahip olmuştur.
Nowadays, unmanned aerial vehicles (UAV) are used in many areas such defense, entertainment, agricultural, mapping and transportation. Since there is no need to have a pilot with the aircraft and it allows autonomous driving, the use of these vehicles has started to be seen in other sectors day by day. In addition, electronics equipment and sensors are getting cheaper with development of technology, which have allowed this sector to develop. The most popular of UAV is quadcopter which it has four propellers. A quadcopter with autonomous flight feature was manufactured for this thesis. In this study, Pixhawk 4 flight control board was selected due to its autonomous flight feature. Autonomous flight was planned and carried out by Mission Planer software, which supports the Pixhawk control board. Four different propellers were designed for the determination of directional stability. Among these designed propellers, the most efficient Quadcopter propeller type was investigated in terms of flight time and directional stability. DAE51, MH42, NACA4412 and NLF0115 airfoils, which were reported to perform well at low Reynolds numbers (Re<100.000) as a result of literature research, were selected for this study. Computational Fluid Dynamics (CFD) and experimental analysis were conducted to reveal the effects of these designed propellers. ANSYS Fluent simulation calculations were made to determine the accuracy of the propeller calculations. In order to reveal a verifiable method for ANSYS Fluent, validation was made with APC 10x7 that has the blade section and aerodynamic performance in literature. The thrust coefficient obtained with mathematical calculation were 4.41% lower for DAE51, 4.91% for MH42, 5.80% for NACA0115 and 5.94% for NLF0115 compared to CFD. After the results revealed that the quadcopter will create the required thrust, test propellers were printed with a 3D printer. Experimental analysis was carried out in an outdoor environment. In the outdoor tests, the wind effects of the propeller were considered. The effects of the propellers designed as DAE51, MH42, NACA4412 and NLF0115 airfoils were compared to the original propeller of the Quadcopter. As a result of the experiments, it was observed that there were no significant differences in the desired and occurring pitch, roll, yaw angles, height and vibration values. In the first and second experiments, the mean deviations were 0.072 m and 0.05 m for DAE51, 0.019 m and 0.13 m for MH42, 0.031 m and 0.03 m for NACA4412, and 0.022 m and 0.028 for NLF0115, respectively. NACA4412 had the best performance in terms of range and directional stability among all propellers.
Nowadays, unmanned aerial vehicles (UAV) are used in many areas such defense, entertainment, agricultural, mapping and transportation. Since there is no need to have a pilot with the aircraft and it allows autonomous driving, the use of these vehicles has started to be seen in other sectors day by day. In addition, electronics equipment and sensors are getting cheaper with development of technology, which have allowed this sector to develop. The most popular of UAV is quadcopter which it has four propellers. A quadcopter with autonomous flight feature was manufactured for this thesis. In this study, Pixhawk 4 flight control board was selected due to its autonomous flight feature. Autonomous flight was planned and carried out by Mission Planer software, which supports the Pixhawk control board. Four different propellers were designed for the determination of directional stability. Among these designed propellers, the most efficient Quadcopter propeller type was investigated in terms of flight time and directional stability. DAE51, MH42, NACA4412 and NLF0115 airfoils, which were reported to perform well at low Reynolds numbers (Re<100.000) as a result of literature research, were selected for this study. Computational Fluid Dynamics (CFD) and experimental analysis were conducted to reveal the effects of these designed propellers. ANSYS Fluent simulation calculations were made to determine the accuracy of the propeller calculations. In order to reveal a verifiable method for ANSYS Fluent, validation was made with APC 10x7 that has the blade section and aerodynamic performance in literature. The thrust coefficient obtained with mathematical calculation were 4.41% lower for DAE51, 4.91% for MH42, 5.80% for NACA0115 and 5.94% for NLF0115 compared to CFD. After the results revealed that the quadcopter will create the required thrust, test propellers were printed with a 3D printer. Experimental analysis was carried out in an outdoor environment. In the outdoor tests, the wind effects of the propeller were considered. The effects of the propellers designed as DAE51, MH42, NACA4412 and NLF0115 airfoils were compared to the original propeller of the Quadcopter. As a result of the experiments, it was observed that there were no significant differences in the desired and occurring pitch, roll, yaw angles, height and vibration values. In the first and second experiments, the mean deviations were 0.072 m and 0.05 m for DAE51, 0.019 m and 0.13 m for MH42, 0.031 m and 0.03 m for NACA4412, and 0.022 m and 0.028 for NLF0115, respectively. NACA4412 had the best performance in terms of range and directional stability among all propellers.
Açıklama
Anahtar Kelimeler
Aerodinamik, Doğrultu Kararlılığı, Drone, İHA, Pervane, Quadcopter, HAD, Aerodynamic, Directional Stability, UAV, Propeller, CFD
Kaynak
WoS Q Değeri
Scopus Q Değeri
Cilt
Sayı
Künye
Çelebi, Y. (2023). Farklı tip quadcopter kanadının uçuş doğrultu kararlılığına etkilerinin deneysel ve sayısal analizi. (Yayınlanmamış Doktora Tezi). Batman Üniversitesi Lisansüstü Eğitim Enstitüsü, Batman.
