Investigation of aerodynamics and longitudinal stability of unmanned aerial vehicle with elevator deflection
Keywords:UAV aerodynamics, horizontal tail and elavator, equilibrium, longlitudinal stability
AbstractThe elevator is usually hinged to the horizontal tail, which acts as a balance and controls the altitude, establishes a steady motion for the aircraft at all lift coefficients. During elevator rotating, the aircraft needs to be stable to establish a new altitude. The horizontal tail has a major role in the value of the airplane’s pitching moment (due to the long arm from the aerodynamic center of the tail to the center of gravity) for the equilibrium and stability of the aircraft. The horizontal tail should be considered as an aerodynamic component behind the main wing, influenced by the wing downwash wing rather than just a minor wing. Therefore, the aim of this study is to examine the flow through unmanned aerial vehicles (UAV) including the main wing, tail and body and to calculate the aerodynamic force on the horizontal tail when rotating the elevator using the Fluent software for the viscous flows. Small disturbance theory was used to calculate the longitudinal stability of the UAV when controlling the elevator. Flying qualities are assessed to show that changes in the aerodynamic characteristics of the wing, tail, fuselage and configuration of the UAV may be required.
L. Smith. Investigation of a modified low-drag body for an alternative wing-body-tail configuration. PhD thesis, University of Pretoria, South Africa, (2017).
A. Paziresh, A. H. Nikseresht, and H. Moradi.Wing-body and vertical tail interference effects on downwash rate of the horizontal tail in subsonic flow. Journal of Aerospace Engineering, 30, (4), (2017). https://doi.org/10.1061/(asce)as.1943-5525.0000704.
D. F. Thomas Jr and W. D. Wolhart. Static longitudinal and lateral stability characteristics at low speed of 45 degree sweptback-midwing models having wings with an aspect ratio of 2, 4, or 6. Technical note 4077, National advisory committee for aeronautics, (1957).
R. C. Nelson. Flight stability and automatic control. McGraw-Hill Education, Inc., (1998).
N. X. Hung. Dynamics and stability of airplane. Vietnam National University, Hanoi, (2004).
J. Welstead. Conceptual design optimization of an augmented stability aircraft incorporating dynamic response performance constraints. PhD thesis, Auburn, Alabama, USA, (2014).
M. Ghoreyshi, I. Greisz, A. Jirasek, and M. Satchell. Simulation and modeling of rigid aircraft aerodynamic responses to arbitrary gust distributions. Aerospace, 5, (2), (2018). https://doi.org/10.3390/aerospace5020043.
D. Keller. Numerical approach aspects for the investigation of the longitudinal static stability of a transport aircraft with circulation control. In New results in numerical and experimental fluid mechanics IX, Springer, (2014), pp. 13–22. https://doi.org/10.1007/978-3-319-03158-3_2.
H. T. B. Ngoc and N. M. Hung. Calculation of transonic flows around profiles with blunt and angled leading edges. Vietnam Journal of Mechanics, 38, (1), (2016), pp. 1–13. https://doi.org/10.15625/0866-7136/38/1/4177.
H. T. B. Ngoc and N. M. Hung. Study of separation phenomenon in transonic flows produced by interaction between shock wave and boundary layer. Vietnam Journal of Mechanics, 33, (3), (2011), pp. 170–181. https://doi.org/10.15625/0866-7136/33/3/210.
M. Mahdi. Prediction of wing downwash using CFD. In 3rd InternationalWorkshop on Numerical Modelling in Aerospace Sciences, Romania, Vol. 7, (2015), pp. 105–111.
E. Seckel and J. J. Morris. The stability derivatives of the Navion aircraft estimated by various methods and derived from flight test data. National Technical Information Service, USA, (1971).
S. Paudel, S. Rana, S. Ghimire, K. K. Subedi, and S. Bhattrai. Aerodynamic and stability analysis of blended wing body aircraft. International Journal of Mechanical Engineering and Applications, 4, (4), (2016), pp. 143–151. https://doi.org/10.11648/j.ijmea.20160404.12.