scholarly journals Design and Fabrication of Voice Controlled Unmanned Aerial Vehicle

2016 ◽  
Vol 5 (3) ◽  
pp. 205
Author(s):  
S. Sakthi Anand ◽  
R. Mathiyazaghan
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Voice Recognition ◽  
Search And Rescue ◽  
Voice Input ◽  
Recognition Process ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
The Voice

<p class="Default">Unmanned Aerial Vehicles have gained well known attention in recent years for a numerous applications such as military, civilian surveillance operations as well as search and rescue missions. The UAVs are not controlled by professional pilots and users have less aviation experience. Therefore it seems to be purposeful to simplify the process of aircraft controlling. The objective is to design, fabricate and implement an unmanned aerial vehicle which is controlled by means of voice recognition. In the proposed system, voice commands are given to the quadcopter to control it autonomously. This system is navigated by the voice input. The control system responds to the voice input by voice recognition process and corresponding algorithms make the motors to run at specified speeds which controls the direction of the quadcopter.</p>

Modeling and control of a quadrotor tail-sitter unmanned aerial vehicles

2021 ◽  
pp. 095965182110504
Author(s):  
Hongbo Xin ◽  
Yujie Wang ◽  
Xianzhong Gao ◽  
Qingyang Chen ◽  
Bingjie Zhu ◽  
...  
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Euler Angle ◽  
Level Flight ◽  
Aerial Vehicles ◽  
Flight Mode ◽  
Aerial Vehicle ◽  
Hover Flight ◽  
And Control

The tail-sitter unmanned aerial vehicles have the advantages of multi-rotors and fixed-wing aircrafts, such as vertical takeoff and landing, long endurance and high-speed cruise. These make the tail-sitter unmanned aerial vehicle capable for special tasks in complex environments. In this article, we present the modeling and the control system design for a quadrotor tail-sitter unmanned aerial vehicle whose main structure consists of a traditional quadrotor with four wings fixed on the four rotor arms. The key point of the control system is the transition process between hover flight mode and level flight mode. However, the normal Euler angle representation cannot tackle both of the hover and level flight modes because of the singularity when pitch angle tends to [Formula: see text]. The dual-Euler method using two Euler-angle representations in two body-fixed coordinate frames is presented to couple with this problem, which gives continuous attitude representation throughout the whole flight envelope. The control system is divided into hover and level controllers to adapt to the two different flight modes. The nonlinear dynamic inverse method is employed to realize fuselage rotation and attitude stabilization. In guidance control, the vector field method is used in level flight guidance logic, and the quadrotor guidance method is used in hover flight mode. The framework of the whole system is established by MATLAB and Simulink, and the effectiveness of the guidance and control algorithms are verified by simulation. Finally, the flight test of the prototype shows the feasibility of the whole system.

scholarly journals MODELLING OF THE UNMANNED AERIAL VEHICLES FLIGHT CONTROL SYSTEM

Aviation ◽  
2021 ◽  
Vol 25 (2) ◽  
pp. 79-85
Author(s):  
Mirosław Adamski
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Aerodynamic Drag ◽  
Unmanned Aircraft ◽  
Simulation Program ◽  
Flight Control System ◽  
Aerial Vehicles ◽  
Aerial Vehicle

The article is an independent work containing the author’s ingenious research methodology and the model of the control system of Unmanned Aerial Vehicles. Furthermore a unique and world first mathematical model of an Unmanned Aerial Vehicle was developed, as well as a simulation program which enabled to investigate the control system of any Unmanned Aerial Vehicles in the tilt duct pitch (altitude), bank (direction), deviation and velocity, depending upon the variable values of the steering coefficient, reinforcement coefficient and the derivative constant. The research program was written in the language of the C++ as the MFC class, on the MS Visual Studio 2010 platform. The main issue resolved in the article is the pioneering research of the process of control during manual and semi-automatic guidance of the Unmanned Aerial Vehicle, with a jet propulsion system to the coordinates of preset points of the flight route. Modelling of the flight control system takes into account: the logical network of operations of the simulation program, the pilot-operator model, the set motion and control deviations as well as the flight control laws. In addition, modeling of the control system takes into account the drive model, engine dynamics, engine thrust, the model of steering actuators and the model of external loads. In contrast, the external load model takes into account the external forces acting on the unmanned aircraft, including gravitational forces and moments, aerodynamic forces and moments, aerodynamic drag, aerodynamic lateral forces, aerodynamic lift forces, aerodynamic heeling moment, mechanism of local angle of attack from damping torque and forces and moments from the engine.

scholarly journals To the question for formation of a block-modular structure of the control system for unmanned aerial vehicles

2021 ◽  
Vol 1 (3) ◽  
pp. 48-64
Author(s):  
Igor Kovalev ◽  
Valy Losev ◽  
Mikhail Saramud ◽  
Andrey Kalinin ◽  
Alexandra Lifar
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Basic Structure ◽  
Modular Structure ◽  
Operating Modes ◽  
Aerial Vehicles ◽  
Generalized Information ◽  
Basic Operating ◽  
Aerial Vehicle

The article discusses an approach to the formation of the basic structure of the control system for unmanned aerial vehicles, based on existing system solutions, typical specifications of the developer's boards. The characteristics of an unmanned aerial vehicle of both air and space class are given. General requirements for hardware and peripheral devices of unmanned aerial vehicles have been formed in accordance with their basic operating modes. Based on the obtained and generalized information about the developer's boards, the block-modular structure of the control system for unmanned aerial vehicles is presented. It includes all the main elements of the system and can be expanded by connecting additional boards. The advantage of this structure for debugging purposes is the presence of an FPGA on the development board.

Information-Measuring Technologies for UAV's Application

2019 ◽  
pp. 274-286
Author(s):  
Vitalii Larin ◽  
Nina Chichikalo ◽  
Georgii Rozorinov ◽  
Ekaterina Larina
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Proximity Sensor ◽  
Information Measuring ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
Current Operation ◽  
Definition Of ◽  
Measuring Unit

This chapter describes two practical examples of sensors application on an unmanned aerial vehicle. The first device is a proximity sensor allowing users to measure the rotating angle of UAV's elevator. The second example discovers a measuring unit established on the UAV and processed measuring information for landing the UAV. To perform exactness control of unmanned aerial vehicles actuating mechanisms, the control system must be supplied by devices providing precision definition of values of current operation factors of those mechanisms.

Combined active flow and flight control systems design for morphing unmanned aerial vehicles

2019 ◽  
Vol 233 (14) ◽  
pp. 5393-5402 ◽  
Author(s):  
Öztürk Özdemir Kanat ◽  
Ertuğrul Karatay ◽  
Oğuz Köse ◽  
Tuğrul Oktay
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Active Flow Control ◽  
Autonomous Flight ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
Active Flow ◽  
First Time

In this article, combined active flow control system and flight control system design for morphing unmanned aerial vehicles is applied for the first time for autonomous flight performance maximization. For this purpose, longitudinal and lateral dynamics modeling of morphing unmanned aerial vehicle having active flow control manufactured in Erciyes University, Faculty of Aeronautics and Astronautics, Model Aircraft Laboratory is considered in order to obtain simulation environments. Our produced morphing unmanned aerial vehicle is called as ZANKA-II, which has a mass of 6.5 kg, range of 30 km, endurance of 0.5 h, and ceiling altitude of 6000 m. von Karman turbulence modeling is used in order to model atmospheric turbulence during flight in both longitudinal and lateral simulation environments. A stochastic optimization method called as simultaneous perturbation stochastic approximation is also applied for the first time in order to obtain optimum dimensions of morphing parameters (i.e. extension ratios of wingspan and tail span), optimum positions of blowers, and optimum magnitudes of longitudinal and lateral controllers' gains (i.e. P, I, and D gains) while minimizing cost index capturing terms for both longitudinal and lateral autonomous flight performances and there exist lower and upper constraints on all optimization variables in the literature.

scholarly journals MECHANISM OF ENSURING SAFE UAV MOVEMENT UNDER THE CONDITIONS OF RADIO ATTACKS

2020 ◽  
Vol 4 (157) ◽  
pp. 178-183
Author(s):  
L. Romaniuk ◽  
I. Chykhira
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Mechanism Of Formation ◽  
Electronic Warfare ◽  
Air Defense ◽  
Defense Systems ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
The Stability

Purpose. The aim of the article is to reveal the mechanism of formation of safe UAV movement in the conditions of radio attacks. Methodology. Scientists from Ternopil National Technical University named after Ivan Pulyuy have consistently developed and studied several mechanisms for the formation of safe movement of unmanned aerial vehicles in radio attacks in order to create a perfect model with which to launch UAVs in areas with high radio attack. As a result of previous work, the mechanism of formation of safe movement of UAVs in the conditions of radio attacks based on methods of increasing the stability of providing information about the route of the unmanned aerial vehicle in the use of REP and air defense systems. Results. The article reveals the mechanism of formation of safe movement of unmanned aerial vehicle in the conditions of radio attacks. Analysis of known solutions in the field of increasing the stability of the control path of unmanned aerial vehicles and electronic suppression demonstrated the relevance of the problem of forming flight routes of unmanned aerial vehicles bypassing opposing enemy areas, taking into account the use of air defense and electronic warfare. The authors emphasize that most drone control tasks are now automated due to their high complexity and versatility. An automated control system operating under the control of a human operator is used as a control factor on an unmanned aircraft. It is emphasized that the main threats to unmanned aerial vehicles in modern conditions are the possibility of their destruction by air defense systems, as well as disruption of the radio communication and control system between the control center and the UAV by electronic suppression. The need for constant tracking of UAV flight by transmitting commands from the launcher is revealed. It is also emphasized the low level of automation of the onboard control system of the unmanned aerial vehicle and the inability to make adequate decisions on information received from onboard sensors in complex situations that require constant monitoring of UAV flight by a human operator. Scientific novelty. For the first time the functional scheme of the UAV recognition mechanism in the conditions of radio attacks is developed and the mechanism of formation of safe movement of the UAV in the conditions of radio attacks which is based on three basic techniques is defined. The first method is the method of clustering the flight zones of an unmanned aerial vehicle according to the degree of control stability. Based on the second method, the authors propose a method of forming the routes of UAV flights, taking into account the location of air defense and electronic warfare. The last link is the method of assessing the stability of providing information about the route of the unmanned aerial vehicle in terms of the use of air defense and electronic warfare. Practical relevance. The results of the work can be implemented in the process of forming the safe movement of UAVs in the conditions of radio attacks. Keywords: unmanned aerial vehicle; air traffic control; space; security; flight.

scholarly journals СИСТЕМА АВТОМАТИЧЕСКОГО УПРАВЛЕНИЯ БЕСПИЛОТНОГО ЛЕТАТЕЛЬНОГО АППАРАТА

2018 ◽  
Vol 9 (4) ◽  
Author(s):  
К. О. Габуев ◽  
В. О. Гонгало ◽  
Н. А. Кучеренко ◽  
А. И. Шипко
Keyword(s):  
Control System ◽  
Automatic Control ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Automatic Control System ◽  
Agricultural Sector ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
The Relationship

The article deals with the use of unmanned aerial vehicles as in industry in general and as in individual branches. The operation of unmanned aerial vehicles in the agricultural sector is described in more detail. The problems existing for today in this sector, as well as the methods of solving these problems with the help of unmanned technologies are given. The important interrelation between the automatic control system and its integration into unmanned aerial vehicles is explained. Detailed description of the technical component of the drone, as well as the relationship between each link of the technical means of automation. An example of the software through which the unmanned aerial vehicle is controlled is given

scholarly journals Study of declination methods while forming the appearance of the surface-to-air unmanned aerial vehicle with a vertical start

2021 ◽  
Vol 24 (3) ◽  
pp. 57-70
Author(s):  
A. V. Vindeker
Keyword(s):  
Control System ◽  
Comparative Analysis ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Thrust Vector Control ◽  
Gas Dynamic ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
Thrust Vector ◽  
Vector Control System

The problem of choosing a rational declination system from alternative variants at the stage of forming the appearance of an unmanned aerial vehicle (UAV) with a vertical launch is considered. Currently, the vertical launch is becoming more widely used for surface-to-air unmanned aerial vehicles, which are considered in this paper. A characteristic initial part of the trajectory of such unmanned aerial vehicles is the declination to the required angular position over a short period of time. The UAV declination process requires the generation of relatively large control moments. Declination of surface-to-air UAVs is implemented by means of moment gas-dynamic control with two main methods – by using the thrust vector control system of the UAV main jet engine or by using special additional gas-dynamic devices. The alternative variants of declination systems for solving the problem under consideration are:– a thrust vector control system with gas rudders installed in the UAV engine nozzle or just behind its cut-off on special pylons;– a pulse propulsion system that creates the UAV declination moment by means of jets of micro-thrusters, which are activated by a special algorithm.In the comparative analysis of declination systems, the criterion for choosing the correct method of declination was the actual near border of the affected zone. The mass minimum of the projected UAV is accepted as the criterion for choosing a rational variant of the declination system. The main relations for calculating the main design parameters of the considered declination systems are given. The appearance parameters of the hypothetical surface-to-air UAV of medium range with alternative declination systems were calculated. A comparative analysis of the results obtained was carried out.

scholarly journals SYNTHESIS OF THE MATHEMATICAL MODEL OF THE AUTOMATIC CONTROL SYSTEM OF THE UNMANNED AIRCRAFT COURSE

2019 ◽  
pp. 152-159
Author(s):  
I. V. Zimchuk ◽  
V. I. Ishchenko ◽  
T. M. Shapar
Keyword(s):  
Mathematical Model ◽  
Computer Simulation ◽  
Control System ◽  
Automatic Control ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Automatic Control System ◽  
Aerial Vehicles ◽  
Aerial Vehicle ◽  
The Mathematical Model

Unmanned aerial vehicles are by far the most promising military and civilian systems. There is a tendency to increase the efforts of a number of leading countries in the development of unmanned aerial vehicles and their complexes. The mathematical model of any system reflects in one way or another its real properties, including the existing limitations. It has been found that one of the most favorable and efficient methods for constructing mathematical models of automatic control systems is to develop them using transfer functions. In order to solve this problem, the article deals with the composition of the control system of a drone. A mathematical model consisting of the joint design of the unmanned aerial vehicle and its automatic control system has been synthesized. The description of the proposed mathematical model of the system is based on the representation of a linear continuous system by the difference equations obtained using the Tustin relation. The mathematical model proposed in the article can be used for the study of typical aircraft whose course management system is built according to the considered structure. The practical significance of the obtained results is the possibility of applying the developed mathematical model to study the dynamics of the change of state and to set up the system of automatic control of the course of the unmanned aerial vehicle through computer simulation. Prospects for further research in this area are computer simulation of an unmanned aerial vehicle control system and estimation of the accuracy of the mathematical model developed.

scholarly journals INTELLECTUALIZED CONTROL SYSTEM FOR UNMANNED AERIAL VEHICLE

2020 ◽  
Vol 1 (1) ◽  
pp. 22-27
Author(s):  
S. LYSENKO ◽  
Keyword(s):  
Fuzzy Logic ◽  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Unmanned Aerial Vehicle ◽  
Degrees Of Freedom ◽  
Large Set ◽  
Motion Models ◽  
External Influences ◽  
Aerial Vehicles ◽  
Aerial Vehicle

The paper presents an intellectualized control system for unmanned aerial vehicles. It is based on the use of the fuzzy logic, implementation of which in the Controller of the unmanned aerial device allowed to track and control the trajectory of its movement. The experimental researches prove the efficiency of the device application of fuzzy logic for control of the drone in conditions of external influences implementation. To construct an intellectualized control system of unmanned aerial vehicles, their structure was considered. The base of the system is used for quadunmanned aerial vehicle, which includes four screws, located symmetrically around the central building. The peculiarity of the drone is that its adjacent screws must spin the opposite one from each other. This requirement is explained by the need to prevent system rotation around its own central axis. Depending on the required trajectory, an important aspect was the ability to set different values of the power of the drone engines. Despite the fact that the simplicity of its structure are characterized, they are able to implement a large set of motion models together with a demonstration of high maneuverability. It is reached the presence of six degrees of freedom, which consist of three progressive and three rotating components to set the trajectory of a movement. In order to solve this problem, it was possible to solve the apparatus of fuzzy logic as the basis of the mathematical model of the system. This allowed to ensure a vague logical control of the fog, and, in turn, intellectualize the behavior of drone in the air in the conditions of external influences on the change of a predetermined trajectory of its movement. At the heart of the Intellectualized unmanned Aerial vehicle control system, two fuzzy controllers were involved in the production of control signals for the command of a UAV flight height and an angle of inclination.

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