Numerical Simulation of the Vertical Landing of Unmanned Aerial Vehicle with Ducted Fan Propulsors by Eddy-Resolving Methods

2020 ◽  
Vol 63 (4) ◽  
pp. 776-780
Author(s):  
D. V. Rybakov ◽  
P. S. Chernyshov ◽  
L. O. Vokin ◽  
N. V. Prodan
Keyword(s):  
Numerical Simulation ◽  
Unmanned Aerial Vehicle ◽  
Ducted Fan ◽  
Aerial Vehicle ◽  
Vertical Landing

scholarly journals A Novel Adaptive Super-Twisting Sliding Mode Control Scheme with Time-Delay Estimation for a Single Ducted-Fan Unmanned Aerial Vehicle

Actuators ◽  
2021 ◽  
Vol 10 (3) ◽  
pp. 54
Author(s):  
Minh-Thien Tran ◽  
Dong-Hun Lee ◽  
Soumayya Chakir ◽  
Young-Bok Kim
Keyword(s):  
Time Delay ◽  
Sliding Mode Control ◽  
Unmanned Aerial Vehicle ◽  
Sliding Mode ◽  
Time Delay Estimation ◽  
Delay Estimation ◽  
Mode Control ◽  
Ducted Fan ◽  
Control Scheme ◽  
Aerial Vehicle

This article proposes a novel adaptive super-twisting sliding mode control scheme with a time-delay estimation technique (ASTSMC-TDE) to control the yaw angle of a single ducted-fan unmanned aerial vehicle system. Such systems are highly nonlinear; hence, the proposed control scheme is a combination of several control schemes; super-twisting sliding mode, TDE technique to estimate the nonlinear factors of the system, and an adaptive sliding mode. The tracking error of the ASTSMC-TDE is guaranteed to be uniformly ultimately bounded using Lyapunov stability theory. Moreover, to enhance the versatility and the practical feasibility of the proposed control scheme, a comparison study between the proposed controller and a proportional-integral-derivative controller (PID) is conducted. The comparison is achieved through two different scenarios: a normal mode and an abnormal mode. Simulation and experimental tests are carried out to provide an in-depth investigation of the performance of the proposed ASTSMC-TDE control system.

Marker images detection algorithm for the unmanned aerial vehicle vertical landing

Trudy MAI ◽  
2021 ◽  
pp. 13-13
Author(s):  
Mikhail Trusfus ◽  
Ilfir Abdullin
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Detection Algorithm ◽  
Aerial Vehicle ◽  
Vertical Landing

Altitude Control Design and Performance Validation for Unmanned Aerial Vehicle with a Single Ducted-Fan

2021 ◽  
Vol 25 (1) ◽  
pp. 23-35
Author(s):  
Minh-Thien Tran ◽  
Hwan-Cheol Park ◽  
Dong-Hun Lee ◽  
Young-Bok Kim
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Control Design ◽  
Ducted Fan ◽  
Aerial Vehicle ◽  
Altitude Control ◽  
And Performance ◽  
Performance Validation

Numerical Simulation and Experimental Verification of the Deposition Concentration of an Unmanned Aerial Vehicle

2019 ◽  
Vol 35 (3) ◽  
pp. 367-376 ◽  
Author(s):  
Qiang Shi ◽  
Hanping Mao ◽  
Xianping Guan
Keyword(s):  
Numerical Simulation ◽  
Flow Field ◽  
Unmanned Aerial Vehicle ◽  
Simulation Analysis ◽  
Three Dimensional ◽  
Laser Scanner ◽  
Utilization Rate ◽  
Droplet Deposition ◽  
Aerial Vehicle ◽  
Motion Characteristics

Abstract. To analyze the droplet deposition under the influence of the flow field of an unmanned aerial vehicle (UAV), a hand-held three-dimensional (3D) laser scanner was used to scan 3D images of the UAV. Fluent software was used to simulate the motion characteristics of droplets and flow fields under the conditions of a flight speed of 3 m/s and an altitude of 1.5 m. The results indicated that the ground deposition concentration in the nonrotor flow field was high, the spray field width was 2.6 m, and the droplet deposition concentration was 50 to 200 ug/cm2. Under the influence of the rotor flow field, the widest deposition range of droplets reached 12.8 m. Notably, the droplet deposition uniformity worsened, and the concentration range of the droplet deposition was 0 to 500 ug/cm2. With the downward development of the downwash flow field, the overall velocity of the flow field gradually decreased, and the influence interval of the flow field gradually expanded. In this article, the droplet concentration was verified under simulated working conditions by a field experiment, thereby demonstrating the reliability of the numerical simulation results. This research could provide a basis for determining optimal UAV operating parameters, reducing the drift of droplets and increasing the utilization rate of pesticides. Keywords: Unmanned aerial vehicle (UAV), Aerial application, Downwash flow field, Droplet deposition, Simulation analysis.

Numerical simulation of a flow around an unmanned aerial vehicle

Mechanika ◽  
2011 ◽  
Vol 17 (2) ◽  
Author(s):  
S. M. A. Meftah ◽  
B. Imine ◽  
O. Imine ◽  
L. Adjlout
Keyword(s):  
Numerical Simulation ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle

Aeroacoustic Analysis of an Unmanned Aerial Vehicle

2007 ◽  
Author(s):  
Peter D. Lysak ◽  
James J. Dreyer ◽  
John B. Fahnline ◽  
Dean E. Capone ◽  
John E. Poremba
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Acoustic Analysis ◽  
Three Dimensional ◽  
Broadband Noise ◽  
Frequency Noise ◽  
Noise Levels ◽  
Boundary Layer Turbulence ◽  
Ducted Fan ◽  
Inflow Turbulence ◽  
Aerial Vehicle

An acoustic analysis of a ducted fan unmanned aerial vehicle (UAV) was conducted to identify the primary aeroacoustic sources and to determine the potential for reducing the radiated noise levels. Computational fluid dynamics was used to determine the three-dimensional flow field through the ducted fan in hover and maneuvering configurations. The flow solutions provided information about the blade relative velocities, spatially non-uniform inflow, inflow turbulence, boundary layer turbulence, and blade wake velocity deficits for use in acoustical models of broadband and blade passing frequency noise. The computational results were in good agreement with experimentally measured noise levels, and showed that the tonal noise was produced primarily by unsteady forces resulting from the non-uniform inflow, while the broadband noise resulted from the inflow turbulence. Based on these findings, design modifications were recommended which offer the potential to reduce the noise by more than 10 dB.

scholarly journals Numerical Simulation of Propeller Slipstream Effect on A Propeller-driven Unmanned Aerial Vehicle

2012 ◽  
Vol 31 ◽  
pp. 150-155 ◽  
Author(s):  
Weijia Fu ◽  
Jie Li ◽  
Haojie Wang
Keyword(s):  
Numerical Simulation ◽  
Unmanned Aerial Vehicle ◽  
Aerial Vehicle

scholarly journals Numerical Simulation of the Motion of an Unmanned Aerial Vehicle

2018 ◽  
Vol 221 ◽  
pp. 05003
Author(s):  
Il’ya O. Akimov ◽  
Vsevolod V. Koryanov
Keyword(s):  
Numerical Simulation ◽  
Mathematical Model ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Software Package ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
Execution Environment ◽  
Controlled Motion

Unmanned aerial vehicles are used for research in many areas: photography and video shooting and so on. The development of unmanned aerial vehicles is directly related to the development of airspace. Today, a mathematical model is required that would describe the movement of such an aircraft with the purpose of predicting, correcting and optimizing it. The paper presents the results of a study of the controlled motion of an unmanned multi-rotor aircraft using the example of a quadrocopter. The study included the development of a law governing the apparatus and its modeling in the form of a software package. The structure of the autopilot, its main contours and parameters of these circuits are considered. After determining the necessary characteristics of the autopilot, modeling of the controlled motion of the quadrocopter in the execution environment was carried out.

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