Comparative Analysis of Propulsive System in Multi-Rotor Unmanned Aerial Vehicle

2019 ◽  
Author(s):  
Balaji Sonaimuthu ◽  
Prabhagaran Panchalingam ◽  
Vijayanandh Raja
Keyword(s):  
Numerical Simulation ◽  
Unmanned Aerial Vehicle ◽  
Pitch Angle ◽  
Design Methodology ◽  
Operating Efficiency ◽  
Forward Speed ◽  
Normal Functioning ◽  
Convergent Nozzle ◽  
Aerial Vehicle ◽  
Ansys Workbench

Abstract In an advanced Multi-rotor Unmanned Aerial Vehicle (UAV), the existing methodology of the propeller and its parametric modification leads to provide the various performance characteristics by inducing the operating efficiency. The subsisting solution for obtaining the thrust, rate of climb and forward speed by proliferating the propeller configuration and modification the design aspects in propeller by varying the pitch angle and consisting parameters in a Multi-rotor UAV. Instead of adding or modifying the design aspects, this article recommends the propeller with attaching Convergent-Divergent (C-D) Nozzle duct, which leads to producing the augmented thrust efficiency than the normal functioning system. And the comparison of the propeller with and without attaching the convergent nozzle duct, divergent nozzle duct, C-D nozzle duct has been analyzed using the numerical simulation and scrutinizing the optimized conceptual design of propeller is done with the help of ANSYS Workbench, where the design methodology is modeled by CATIA. By the result of the simulation, it leads to provide the efficient characteristics and design aspects of the Multi-rotor Unmanned Aerial Vehicle.

scholarly journals Improvement in energy conversion for unmanned aerial vehicle charging pad

2020 ◽  
Vol 17 (2) ◽  
pp. 767
Author(s):  
M. R. AL-Obaidi ◽  
M. A. Mustafa ◽  
W.Z.W. Hassan ◽  
N. Azis ◽  
A. H. Sabry ◽  
...  
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Design Methodology ◽  
Font Size ◽  
Contact Charging ◽  
Charging Station ◽  
Ground Station ◽  
Landing Platform ◽  
Aerial Vehicle ◽  
Fully Automatic ◽  
Software And Hardware

<span style="font-size: 9pt; font-family: 'Times New Roman', serif;">An efficient charging station is a necessity for Unmanned Aerial Vehicle (UAV) systems. However, if that implementation adds more complexity and onboard weight, then that exercise becomes a burden rather than a benefit since UAV's engineers aim to improve efficiency by reducing the energy consumed by the software and hardware of the complete aeronautical system. This article recommends a fully automatic contact charging station for UAVs, which can charge UAVs and thus resolve flight endurance restrictions of the UAV. The ground station consists of square copper plates that are positively and negatively polarized successively in a chessboard with particular sizes to guarantee electric contact at the landing. The design methodology used with the loading station takes into account the differences in UAV orientation once the platform has landed. In addition, this innovation uses independent charging after touchdown. Thus, this technology relaxes common flight times and help to enhance general mission times. This paper presents a unique charging platform in a “chessboard” configuration, which is devised as an interconnecting interface to facilitate the charging process and overcome inaccuracies with the landing. The solution devised in this research requires few components and presents two power source options (solar &amp; mains power). Additionally, this work presents, to the best of our knowledge, a uniquely innovative recharging landing platform, which incidentally requires no additional software or changes to the UAV’s onboard software settings</span><span style="font-size: 9pt; font-family: Arial, sans-serif;">.</span>

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.

scholarly journals Computational optimal launching control for balloon-borne solar-powered unmanned aerial vehicles in near-space

2019 ◽  
Vol 103 (1) ◽  
pp. 003685041987775 ◽  
Author(s):  
Yanpeng Hu ◽  
Yanping Yang ◽  
Xiaoping Ma ◽  
Shu Li
Keyword(s):  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Pitch Angle ◽  
Control Variable ◽  
Maximum Speed ◽  
Near Space ◽  
Aerial Vehicles ◽  
Axial Acceleration ◽  
Aerial Vehicle ◽  
Solar Powered

The near-space solar-powered unmanned aerial vehicle has broad prospects in application owing to its high altitude long-endurance performance. Launching solar-powered unmanned aerial vehicle into the near-space with balloon-borne approach has advantages over the traditional sliding take-off methods, in that it is able to quickly and safely cross the turbulent zone. In this article, we investigate the control technology of balloon-borne launching for the solar-powered unmanned aerial vehicles. First, the motion of the launching process is divided into longitudinal and lateral-directional motion, with the longitudinal process and its equation addressed in detail. We then analyze the flight state and restriction conditions that the unmanned aerial vehicle should meet during the process. Second, the target variables and constraints are selected to formulate the optimization problem. The control variable parameterization method is applied to find the optimal pitch angle in the releasing-and-pulling process. More explicitly, a three-channel attitude stabilization controller is designed, in which the longitudinal channel takes the optimal pitch angle as the pitch instruction, the transverse channel carries out the zero control of the inclination angle, and the course channel takes the stabilization control, respectively. Numerical simulation results show that our proposed control design is capable of accelerating the solar-powered unmanned aerial vehicles from the vertical state and pulling them up to the horizontal cruising flight state, with the flight angle of attack, the maximum speed, and the maximum axial acceleration in the pulling process all within the designed range.

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

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.

scholarly journals Optimasi Kendali PID menggunakan Algoritma Genetika untuk Penerbangan Quadrotor

2017 ◽  
Vol 7 (2) ◽  
pp. 173
Author(s):  
Khalaqas Hakiim ◽  
Andi Dharmawan ◽  
Faizah Faizah
Keyword(s):  
Genetic Algorithm ◽  
Steady State ◽  
Unmanned Aerial Vehicle ◽  
Pitch Angle ◽  
Pid Controller ◽  
Algorithm Optimization ◽  
Research Designs ◽  
Result Show ◽  
Aerial Vehicle ◽  
Yaw Angle

Quadrotor is square-form unmanned aerial vehicle (UAV) type with four motor in each arms. Quadrotor has ability to take-off and landing vertically. This research designs and creates a system that capable to stabilize the quadrotor flight also able to maintain roll, pitch and yaw angle using PID controller optimized by genetic algorithm, one of evolutionary algorithms.PID is a common applied controller including to control the quadrotor. Tunning or setting PID parameter process is needed to obtain fit PID parameters. Tunning is very important to reach quadrotor flight stability. This research applies Ziegler-Nichols tunning to obtain PID parameters. Then the PID parameters will be a reference for genetic algorithm optimization process to obtain the suitest PID parameter to control roll, pitch ,and yaw angle.Optimization process result show quadrotor controller capable to reach stability with steady state error for pitch angle in range 2,34 degree conterclockwise to 3,37 degree clockwise, for roll angle in range 2,99 degreee counterclockwise to 2,27 degree clockwise, and for yaw angle in range 8,39 degree counterclockwise to 3,89 degree clockwise.

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