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

Year 2019, Volume: 3 Issue: 2, 106 - 112, 25.12.2019

Mustafa Önal , Sezer Çoban , Ahmet Yapıcı , Hasan Hüseyin Bilgiç

https://doi.org/10.30518/jav.633775

Cited By: 2

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.

Keywords

UAV, range, flight parameter, energy consumption, cruise flight

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

Abstract

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.

Keywords

İHA, menzil, uçuş parametresi, enerji tüketimi, seyir uçuşu

References

• [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.