SavedAdd your journal

Journals / Journal of Aviation / 2019 / Volume: 3 Issue: 2

Determination of the Optimum Flight Parameters for Maximum Range and Minimum Power Requirement of a Vertical Take-Off and Landing UAV

Dikey İniş Kalkış Yapabilen Bir İHA’nın Azami Menzili ve Asgari Güç Gereksinimi İçin En Uygun Uçuş Parametrelerinin Belirlenmesi

Mustafa Önal(İSKENDERUN TEKNİK ÜNİVERSİTESİ)0000-0002-4238-6947
Sezer Çoban(İSKENDERUN TEKNİK ÜNİVERSİTESİ)0000-0001-6750-5001
Ahmet Yapıcı(İSKENDERUN TEKNİK ÜNİVERSİTESİ)0000-0003-4274-2697
Hasan Hüseyin Bilgiç(MUSTAFA KEMAL ÜNİVERSİTESİ, İSKENDERUN SİVİL HAVACILIK YÜKSEKOKULU)0000-0001-6006-8056
Pages
—
Publication Date
2019-12-25
🏛️Bibliographic metadata and full text access for this article are provided via DergiPark.
DergiPark Record ↗
✨

AI Summary & Key Takeaways

AI Insight
⚡ TL;DR(Too Long; Didn't Read)

As a result of the analyzes, the most suitable angle of attack for minimum power requirement and maximum range was obtained as 12° and 8°, respectively.

📌 3 Key Takeaways

🎯
Objective & Hypothesis:When designing unmanned aerial vehicles (UAVs), it is taken into consideration that certain features are met.
📊
Key Findings & Data:In some UAVs, models are designed according to the maximum speeds that can be reached, while in others, they are designed according to the maximum lifting forces.
💡
Conclusion & Impact:As a result of the analyzes, the most suitable angle of attack for minimum power requirement and maximum range was obtained as 12° and 8°, respectively.
🔬Design:Modeling & Simulation
📍Scope:Comprehensive Sample
⚙️Variables:UAV · range · flight parameter

Abstract

When designing unmanned aerial vehicles (UAVs), it is taken into consideration that certain features are met. In some UAVs, models are designed according to the maximum speeds that can be reached, while in others, they are designed according to the maximum lifting forces. In this study, flight parameters were calculated by aerodynamic analysis performed in an analysis program in order to reach the maximum range of a designed UAV and then the UAV was produced. During the aerodynamic analysis, first the wing profile and then the whole body were analyzed. As a result of the analyzes, the most suitable angle of attack for minimum power requirement and maximum range was obtained as 12° and 8°, respectively.

Özet

İnsansız hava araçları tasarlanırken bir takım özelliklerin karşılanması göz önünde bulundurulur. Bazı insansız hava araçlarında ulaşılabilecek maksimum hızlara göre modeller tasarlanırken bazılarında ise maksimum taşıma kuvvetlerinin oluşması istenebilir. Bu çalışmada tasarımı yapılmış bir insansız hava aracının maksimum menzile ulaşabilmesi için uçuş parametreleri bir analiz programında yapılan aerodinamik analiz yardımı ile hesaplanmış ve ardından İHA’nın üretimi yapılmıştır. Aerodinamik analizler yapılırken öncelikle kanat profilinin daha sonra tüm gövdenin analizi yapılmıştır.

🔖

Cite This Article

Önal, M., Çoban, S., Yapıcı, A., Bilgiç, H. H. (2019). Determination of the Optimum Flight Parameters for Maximum Range and Minimum Power Requirement of a Vertical Take-Off and Landing UAV. Journal of Aviation, Volume: 3 Issue: 2. https://doi.org/10.30518/jav.633775

📄 Full Text PDF Viewer

📄

PDF görüntüleyici hazırlanıyor...

References (12)

  1. J. Mariens, “Wing Shape Multidisciplinary Design Optimization,” pp.12-61, Master Thesis, Delft University of Technology, 2012.
  2. He, Y., Fu, M. C., Marcus, S. I., (2003) “Convergence of Simultaneous Perturbation Stochastic Approximation for Non-Differentiable Optimization”, IEEE Transactions on Aerospace and Electronic Systems, 48 (8):1459–1463.
  3. Kuo, B. C. (1963). Analysis and synthesis of sampled-data control systems. Prentice-Hall
  4. H. Yeo, W. Johnson, “Performance and Design Investigation ofHeavy Lift Tilt-Rotor with Aerodynamic Interference Effects,”Journal of Aircraft, vol. 46, no. 4, pp. 1231–1239, 2009. doi:10.2514/1.40102
  5. Çoban, S, Bilgiç, H, Oktay, T. (2019). Designing, Dynamic Modeling and Simulation of ISTECOPTER. Journal of Aviation, 3 (1), 38-44. DOI: 10.30518/jav.564376
  6. Çoban, S, Oktay, T. (2018). Unmanned Aerial Vehicles (UAVs) According to Engine Type. Journal of Aviation, 2 (2), 177-184. DOI: 10.30518/jav.461116
  7. Oktay T., Çoban S., "Simultaneous Longitudinal and Lateral Flight Control Systems Design For Both Passive and Active Morphing TUAVs ", ELEKTRONİKA IR ELEKTROTECHNİKA, vol.23, no.5, pp.15-20, 2017
  8. Oktay, Tugrul; Coban, Sezer. Lateral Autonomous Performance Maximization of Tactical Unmanned Aerial Vehicles by Integrated Passive and Active Morphing. International Journal of Advanced Research in Engineering, [S.l.], v. 3, n. 1, p. 1-5, mar. 2017. ISSN 2412-4362.
  9. Nelson, R. C. (1998). Flight stability and automatic control (Vol. 2). WCB/ McGraw Hill.
  10. Çoban, S, Bilgiç, H, Oktay, T. (2019). Designing, Dynamic Modeling and Simulation of ISTECOPTER. Journal of Aviation, 3 (1), 38-44. DOI: 10.30518/jav.564376
  11. Çoban, S, Oktay, T. (2018). Unmanned Aerial Vehicles (UAVs) According to Engine Type. Journal of Aviation, 2 (2), 177-184. DOI: 10.30518/jav.461116
  12. Oktay T., Çoban S., "Simultaneous Longitudinal and Lateral Flight Control Systems Design For Both Passive and Active Morphing TUAVs ", ELEKTRONİKA IR ELEKTROTECHNİKA, vol.23, no.5, pp.15-20, 2017