Using Ansys for Design and Numerical Study of a Specific Fixed Wing UAV

2018 ◽  
Vol 55 (4) ◽  
pp. 652-657 ◽  
Author(s):  
Gabriel Murariu ◽  
Razvan Adrian Mahu ◽  
Adrian Gabriel Murariu ◽  
Mihai Daniel Dragu ◽  
Lucian P. Georgescu ◽  
...  
Keyword(s):  
Numerical Simulations ◽  
Unmanned Aerial Vehicle ◽  
Numerical Study ◽  
Flight Time ◽  
Cluster System ◽  
Numerical Results ◽  
Operational Performance ◽  
Gliding Flight ◽  
Aerial Vehicle ◽  
Constant Altitude

This article presents the design of a specific unmanned aerial vehicle UAV prototype own building. Our UAV is a flying wing type and is able to take off with a little boost. This system happily combines some major advantages taken from planes namely the ability to fly horizontal, at a constant altitude and of course, the great advantage of a long flight-time. The aerodynamic models presented in this paper are optimized to improve the operational performance of this aerial vehicle, especially in terms of stability and the possibility of a long gliding flight-time. Both aspects are very important for the increasing of the goals� efficiency and for the getting work jobs. The presented simulations were obtained using ANSYS 13 installed on our university� cluster system. In a next step the numerical results will be compared with those during experimental flights. This paper presents the main results obtained from numerical simulations and the obtained magnitudes of the main flight coefficients.

Distributed task allocation with critical tasks and limited capacity

Robotica ◽  
2021 ◽  
pp. 1-25
Author(s):  
An Zhang ◽  
Mi Yang ◽  
Bi Wenhao ◽  
Fei Gao
Keyword(s):  
Numerical Simulations ◽  
Unmanned Aerial Vehicle ◽  
Task Allocation ◽  
Network Capacity ◽  
Allocation Problem ◽  
Limited Capacity ◽  
Performance Impact ◽  
Task List ◽  
Aerial Vehicle ◽  
Traditional Performance

Abstract This paper considers the task allocation problem under the requirement that the assignments of some critical tasks must be maximized when the network capacity cannot accommodate all tasks due to the limited capacity for each unmanned aerial vehicle (UAV). To solve this problem, this paper proposes an extended performance impact algorithm with critical tasks (EPIAC) based on the traditional performance impact algorithm. A novel task list resizing phase is developed in EPIAC to deal with the constraint on the limited capacity of each UAV and maximize the assignments of critical tasks. Numerical simulations demonstrate the outstanding performance of EPIAC compared with other algorithms.

scholarly journals Long endurance electric multirotor Unmanned Aerial Vehicle

2020 ◽  
Vol 32 ◽  
pp. 99-109
Author(s):  
Dimo Zafirov
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Flight Time ◽  
Different Types ◽  
Aerial Vehicle ◽  
Long Endurance

The article presents an algorithm for development of a Long endurance electric multirotor unmanned aerial vehicle. Calculations for usage of different types of electric batteries have been made and dependencies of flight time for different weights of batteries have been obtained. Options for quadcopter and sixcopter have been considered.

Emerging approaches to support dynamic mission planning: survey and recommendations for future research

2020 ◽  
pp. 154851291989875
Author(s):  
Matthew Henchey ◽  
Scott Rosen
Keyword(s):  
Unmanned Aerial Vehicle ◽  
Department Of Defense ◽  
Flight Time ◽  
Flight Path ◽  
Mission Planning ◽  
Future Research ◽  
Problem Space ◽  
New Information ◽  
Algorithmic Support ◽  
Aerial Vehicle

In the Department of Defense, unmanned aerial vehicle (UAV) mission planning is typically in the form of a set of pre-defined waypoints and tasks, and results in optimized plans being implemented prior to the beginning of the mission. These include the order of waypoints, assignment of tasks, and assignment of trajectories. One emerging area that has been recently identified in the literature involves frameworks, simulations, and supporting algorithms for dynamic mission planning, which entail re-planning mid-mission based on new information. These frameworks require algorithmic support for flight path and flight time approximations, which can be computationally complex in nature. This article seeks to identify the leading academic algorithms that could support dynamic mission planning and recommendations for future research for how they could be adopted and used in current applications. A survey of emerging UAV mission planning algorithms and academic UAV flight path algorithms is presented, beginning with a taxonomy of the problem space. Next, areas of future research related to current applications are presented.

Numerical Study on the Influence of the Corner Curvature of Circular Micropillar on Microdroplet Size via a Dewetting Process

2014 ◽  
Vol 493 ◽  
pp. 111-116
Author(s):  
Bambang Arip Dwiyantoro
Keyword(s):  
Numerical Simulations ◽  
Flow Pattern ◽  
Numerical Study ◽  
Numerical Results ◽  
Viscous Force ◽  
Curvature Radius ◽  
Capillary Effect ◽  
Dewetting Process ◽  
Water Front

The influence of the corner curvature of circular micropillar on microdroplet formation by a dewetting process was numerically investigated. The diameter of the microdroplets is mainly determined by the capillary effect and viscous force contributed by the wetted surface i.e. on the top surface of micropillar magnifies, which slows down the movement of water front attached to the top surface of micropillar. The numerical simulations showed that the corner curvature of the micropillars play an important role in determining the flow pattern of the dewetting process, especially the evolution and movement of the meniscus across the micropillar before a microdroplet is formed. The water front on the top surface of micropillar with right-angle corner moves much slower than that on the micropillar with round corner. The numerical results also indicate that the curvature radius (r) on circular micropillar is one of the parameters governing the size of the microdroplets formed on the top surface of the micropillars after the dewetting process, while the microdroplet diameter decreases with the increase of the dimensionless of curvature corner.

scholarly journals Stochastic Drift Counteraction Optimal Control of a Fuel Cell-Powered Small Unmanned Aerial Vehicle

Energies ◽  
2021 ◽  
Vol 14 (5) ◽  
pp. 1304
Author(s):  
Jiadi Zhang ◽  
Ilya Kolmanovsky ◽  
Mohammad Reza Amini
Keyword(s):  
Optimal Control ◽  
Fuel Cell ◽  
Power Management ◽  
Unmanned Aerial Vehicle ◽  
Power Output ◽  
Optimal Policy ◽  
Flight Time ◽  
Aerial Vehicle ◽  
Optimal Coordination ◽  
Value Iterations

This paper investigates optimal power management of a fuel cell hybrid small unmanned aerial vehicle (sUAV) from the perspective of endurance (time of flight) maximization in a stochastic environment. Stochastic drift counteraction optimal control is exploited to obtain an optimal policy for power management that coordinates the operation of the fuel cell and battery to maximize the expected flight time while accounting for the limits on the rate of change of fuel cell power output and the orientation dependence of fuel cell efficiency. The proposed power management strategy accounts for known statistics in transitions of propeller power and climb angle during the mission, but does not require the exact preview of their time histories. The optimal control policy is generated offline using value iterations implemented in Cython, demonstrating an order of magnitude speedup as compared to MATLAB. It is also shown that the value iterations can be further sped up using a discount factor, but at the cost of decreased performance. Simulation results for a 1.5 kg sUAV are reported that illustrate the optimal coordination between the fuel cell and the battery during aircraft maneuvers, including a turnpike in the battery state of charge (SOC) trajectory. As the fuel cell is not able to support fast changes in power output, the optimal policy is shown to charge the battery to the turnpike value if starting from a low initial SOC value. If starting from a high SOC value, the battery energy is used till a turnpike value of the SOC is reached with further discharge delayed to later in the flight. For the specific scenarios and simulated sUAV parameters considered, the results indicate the capability of up to 2.7 h of flight time.

scholarly journals Sistem Kontrol Pesawat Tanpa Awak Untuk Menentukan Waypoint Berbasis Ardupilot

2021 ◽  
Vol 2 (2) ◽  
pp. 80-86
Author(s):  
Putri Rachmawati ◽  
Muhammad Haydar Asyam
Keyword(s):  
Control System ◽  
Remote Control ◽  
Computer System ◽  
Long Range ◽  
Unmanned Aerial Vehicle ◽  
Flight Time ◽  
Flight Mode ◽  
Model Aircraft ◽  
Aerial Vehicle ◽  
Remote System

An unmanned Aerial Vehicle (UAV) is a type of unmanned aerial vehicle which is controlled by a remote system. This type of aircraft is usually controlled by remote control from outside the plane and can also move automatically based on a program that has been programmed on the computer system. In this study, a control system with autopilot and remote control is used. This study aims to apply the ardupilot system to the super heavy model aircraft with a long-range flight mode control system using the Futaba T8J (8 channel) radio control. The results of this study took a flight time of 15.02 minutes with an altitude of 30 meters, a waypoint radius of 20 meters with a speed of 10 m / s.

scholarly journals Flying UltraSonic – A new way to measure the wind

2019 ◽  
Author(s):  
Martin Hofsäß ◽  
Dominique Bergmann ◽  
Jan Denzel ◽  
Po Wen Cheng
Keyword(s):  
Wind Speed ◽  
Unmanned Aerial Vehicle ◽  
Ultrasonic Sensor ◽  
Great Effort ◽  
Flow Conditions ◽  
Measuring Methods ◽  
Ultrasonic Anemometer ◽  
Aerial Vehicle ◽  
Constant Altitude ◽  
Good Agreement

Abstract. Measurements of flow conditions at complex sites that are difficult to install a met mast are expensive and can only be carried out with great effort. Concepts and new measuring methods are needed to evaluate these sites. This article presents an experiment in which an unmanned aerial vehicle (UAV), more precisely a helicopter, was equipped with a standard 3-D ultrasonic anemometer. This UAV was positioned closed to a meteorological measuring mast and remained stationary at a constant altitude to measure the wind speed components. The data of the UAV were compared with the measurements of an ultrasonic sensor installed on the met mast. The measurements shows a deviation of 0.1 m/s for the horizontal speed. A comparison of the PSDs shows a very good agreement.

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