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.

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.

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 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>

Flight Control System Onboard Embedded Software for Small Unmanned Aerial Vehicles

2010 ◽  
Vol 20-23 ◽  
pp. 1528-1533
Author(s):  
Jin Jun Rao ◽  
Tong Yue Gao ◽  
Zhen Jiang ◽  
Zhen Bang Gong
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicles ◽  
Flight Control ◽  
Genetic Architecture ◽  
Flight Control System ◽  
Aerial Vehicles ◽  
Operation Procedure ◽  
Function Modules ◽  
Task Processing ◽  
And Function

The onboard software of the flight control system (FCS) plays important role for small unmanned aerial vehicles’ performance. In this paper, the characteristics difficulties of the FCS software are analyzed firstly, then the compositions of the software are introduced using HIPO method. A genetic architecture of onboard software is presented to coordinate and organize the software and function modules, and an unique task scheduling strategy is designed and applied to realize multi-task processing. Finally, on the basis of the elementary operation procedure of the software, the flight experiment is implemented, and the feasibility and reliability of the onboard software is validated.

scholarly journals APPROACH TO INCREASING THE SURVIVABILITY OF CLASS I UNMANNED AERIAL VEHICLE IN EMERGENCY OPERATIONS

2020 ◽  
pp. 54-63
Author(s):  
O. M. Pereguda ◽  
A. V. Rodionov ◽  
S. P. Samoilyk
Keyword(s):  
Information System ◽  
Unmanned Aerial Vehicles ◽  
Control Systems ◽  
Unmanned Aerial Vehicle ◽  
Unmanned Aircraft ◽  
Class I ◽  
Control Action ◽  
Emergency Operations ◽  
Aerial Vehicles ◽  
Aerial Vehicle

The article proposes an approach to increasing the survivability of class I unmanned aerial vehicles in emergency operations which involves development of an onboard information system for identifying emergency occasions in flight and the synthesis of a control action on the unmanned aircraft in case of hazardous factors influence. As the result of the analysis of the main trends in the development of unmanned aerial vehicles onboard control systems, it was found that the leading countries are paying significant attention to increasing their intellectualization level. This is necessary to ensure the fulfilment of complex tasks that are assigned to modern unmanned aerial vehicles in the military and civilian spheres. The main directions of such researches are identifying the problem of swarm application of unmanned aerial vehicles and expanding the capabilities of onboard control systems maintain automatically the values of certain parameters when the flight conditions changes. As the approach to increasing the survivability of a class I unmanned aerial vehicle, a vision of an onboard information system for identifying emergency occasions in flight and synthesis of control action is proposed, the functional purpose of its components is described. It is suggested that this system will be comprised of a subsystem for identifying emergency cases in flight and determining the class I unmanned aerial vehicle threat level and a subsystem for synthesizing control action. Governing documents and regulations for the state aviation of Ukraine determines the list of aircraft emergency occasions. Article mentions the necessity of detailing emergency occasions in flight, which are typical for class I unmanned aerial vehicles and an approach to their classification is proposed. A vision of the nearest partial scientific tasks and a list of expected scientific results of research in this direction are given.

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