Simultaneous Design of a Small UAV (Unmanned Aerial Vehicle) Flight Control System and Lateral State Space Model

Çoban, Sezer; Oktay, Tugrul

doi:10.30518/jav.461365

Cited by 7 publications

(4 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…y ¼ 0 0 0 0 0 0 0 1 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 1 The lateral flight state space model is given as output because 1 (roll) and w (yaw) are followed in the output matrix [equations ( 15) and ( 16)] ( Çoban and Oktay, 2018).…”

Section: Autopilot System and Control Algorithmmentioning

confidence: 99%

“…In the longitudinal state space model output matrix, the outputs followed in this study are given as outputs, as z (upward) and θ (pitch) are followed [equations (13) and (14)] (Kose and Oktay, 2019a, 2019b). The lateral flight state space model is given as output because ∅ (roll) and φ (yaw) are followed in the output matrix [equations (15) and (16)] (Çoban and Oktay, 2018). In classical control, phase forward or reverse compensators are designed, and a pole and zero are added to the system (Oktay et al , 2017).…”

Section: Autopilot System and Control Algorithmmentioning

confidence: 99%

See 1 more Smart Citation

Simultaneous arm morphing quadcopter and autonomous flight system design

Kose,

Oktay,

Özen

2023

AEAT

View full text Add to dashboard Cite

Purpose The purpose of this paper is to obtain values that stabilize the lateral and longitudinal flight of the quadrotor for which the morphing amount and the best Proportional-Integral-Derivative (PID) coefficients are determined by using the simultaneous perturbation stochastic approximation (SPSA) optimization algorithm. Design/methodology/approach Quadrotor consists of body and arms; there are propellers at the ends of the arms to take off and rotors that rotate them. By reducing the angle between mechanism 1 and the rotors with the horizontal plane, the angle between mechanism 2 and the arms, the rotors rise and different configurations are obtained. Conventional multi-rotor aircraft has a fixed fuselage and does not need a tail rotor to change course as helicopters do. The translational and rotational movements are provided by the rotation of the rotors of the aircraft at different speeds by creating moments about the geometric center in 6-degree-of-freedom (DOF) space. These commands sent from the ground are provided by the flight control board in the aircraft. The longitudinal and lateral flight stability and properties of different configurations evaluated by dynamic analysis and simulations in 6 DOF spaces are investigated. An algorithm and PID controller are being developed using SPSA to achieve in-flight position and attitude control of an active deformable aircraft. The results are compared with the results of the literature review and the results of the previous article. Findings With SPSA, the best PID coefficients were obtained in case of morphing. Research limitations/implications The effects of quadrotor arm height and hub angle changes affect flight stability. With the SPSA optimization method presented in this study, the attitude is quickly stabilized. Practical implications With the optimization method, the most suitable PID coefficients and angle values for the lateral and longitudinal flight stability of the quadrotor are obtained. Social implications The transition rate and PID coefficients are determined by using the optimization method, which is advantageous in terms of cost and practicality. Originality/value With the proposed method, the aircraft can change shape to adapt to different environments, and the parameters required for more stable flight for each situation will be calculated, and this will be obtained more quickly and safely with the SPSA optimization method.

show abstract

Section: Autopilot System and Control Algorithmmentioning

confidence: 99%

Section: Autopilot System and Control Algorithmmentioning

confidence: 99%

Simultaneous arm morphing quadcopter and autonomous flight system design

Kose,

Oktay,

Özen

2023

AEAT

View full text Add to dashboard Cite

show abstract

“…Figure 12. Hover Flight PID Block [8] In order to integrate the components that we will use, the necessary circuit diagram is made in the olup Fritzing 'program and the parts included in the program are combined as electronic circuit diagram as shown in figure 13.…”

Section: Flight Control Systemmentioning

confidence: 99%

Designing, Dynamic Modeling and Simulation of ISTECOPTER

Çoban

Bilgiç²,

Oktay³

2019

Journal of Aviation

Self Cite

View full text Add to dashboard Cite

In this study, ISTECOPTER was modeled, performance evaluations were made and control system was designed. ISTECOPTER is a four-rotor Unmanned Aerial Vehicle (UAV) consisting of the abbreviation of Iskenderun Technical University and the combination of the words copter. For the control system, lateral, longitudinal and vertical takeoff of the UAV (Unmanned Aerial Vehicle) and the separate mathematical model of the descent operations were extracted and expressed as the state space model. The mathematical model of the wind distortions that will affect the aircraft during the flight was created and the situation was added to the space model. Proportional Integral Derivative (PID) control algorithm was used as a control. The unmanned aircraft was modeled in Solidworks and the simulations in Matlab / Simulink program. the İSTECOPTER is planned to have 4 brushless DC motors and has a weight of approximately 1.5 kg without load and 1 kg of payload is planned.

show abstract

“…These data can also be tested with simulation programs that provide the required conditions. The model can then be linearized and adapted to the desired control design (Çoban and Oktay, 2018;Fahlstrom and Gleason, 1998). In the same way, it is also possible to design a general control system by using the model lineerization method for different flight conditions (Kumon et al, 2006).…”

Section: Introductionmentioning

confidence: 99%

Different Autopilot Systems Design For a Small Fixed Wing Unmanned Aerial Vehicle

Çoban

Bilgiç²

2019

European Journal of Science and Technology

Self Cite

View full text Add to dashboard Cite

The aim of this study is to design an autopilot system for Unmanned Aerial Vehicle (UAV) in a small size and to compare the efficiency of the systems designed with different methods. For this purpose, linearized equations of motion for a small size UAV has beeen firstly obtained. Then the state space equations are used to check the stability characteristics of the UAV. Using the classical method, the longitudinal pitch angle, altitude and speed controller are designed for separate transfer functions according to the location curve of the roots and the desired response values. PID values were determined by considering the response of the system using classical methods. On the other hand, a feedback control system has been designed to improve the stability of different lines. And also an orientation controller has been designed. New approach proposed in the study is Adaptive Network Based Fuzzy Inference Systems (ANFIS) controller. In this study, a new controller approach based on fuzzy logic is proposed. Four data sets, PID control inputs and control sign have been obtained for the design of the proposed controller. These data sets have been used for training the fuzzy controller. As a result; It is presented with graphs that the proposed method is applicable and gives successful results.

show abstract

Simultaneous Design of a Small UAV (Unmanned Aerial Vehicle) Flight Control System and Lateral State Space Model

Cited by 7 publications

References 7 publications

Simultaneous arm morphing quadcopter and autonomous flight system design

Simultaneous arm morphing quadcopter and autonomous flight system design

Designing, Dynamic Modeling and Simulation of ISTECOPTER

Different Autopilot Systems Design For a Small Fixed Wing Unmanned Aerial Vehicle

Contact Info

Product

Resources

About