Improving Autonomous Performance of a Passive Morphing Fixed Wing UAV

Çoban, Sezer

doi:10.5755/j01.itc.49.1.23275

Cited by 8 publications

(4 citation statements)

References 11 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…In fixed-wing UAVs, morphing is accomplished by changing the wing plan shapes (Oktay and Eraslan, 2022) and in rotarywing UAVs, it is usually done by changing arm lengths. Coban et al (2020) used both passive and active morphing for fixedwing UAVs to maximize both longitudinal and lateral flight performance. Çoban and Oktay (2023) designed and manufactured a fixed-wing UAV with active and passive morphing.…”

Section: Introductionmentioning

confidence: 99%

Stochastic optimal tuning for flight control system of morphing arm octorotor

Kose

2024

AEAT

View full text Add to dashboard Cite

Purpose This study aims to discuss the simultaneous longitudinal and lateral flight control of the octorotor, a rotary wing unmanned aerial vehicle (UAV), for the first time under the effect of morphing and to improve autonomous flight performance. Design/methodology/approach This study aims to design and control the octorotor flight control system with stochastic optimal tuning under morphnig effect. For this purpose, models of different arm lengths of the octorotor were drawn in the Solidworks program. The morphing was carried out by simultaneously lengthening or shortening the arm lengths of the octorotor. The morphing rate was estimated by using simultaneous perturbation stochastic approximation (SPSA). The stochastic gradient descent algorithm, which is frequently used in machine learning, was used to estimate the changing moments of inertia with the change of arm lengths. The proportional integral derivative (PID) controller has been preferred as an octorotor control algorithm because of its simplicity of structure. The PID gains required to control both longitudinal and lateral flight were also estimated with SPSA. Findings With SPSA, three longitudinal flight PID gains, three lateral flight PID gains and one morphing ratio were estimated. PID gains remained within the limits set for SPSA, giving satisfactory results. In addition, the cost index created was 93% successful. The gradient descent algorithm used for the moment of inertia estimation achieved the optimum result in 1,570 iterations. However, in the simulations made with the obtained data, longitudinal and lateral flight was successfully carried out. Originality/value Octorotor longitudinal and lateral flight control was performed quickly and effectively with the proposed method. In addition, the desired parameters were obtained with the optimization methods used, and the longitudinal and lateral flight of the octorotor was successfully carried out in the desired trajectory.

show abstract

Section: Introductionmentioning

confidence: 99%

Stochastic optimal tuning for flight control system of morphing arm octorotor

Kose

2024

AEAT

View full text Add to dashboard Cite

show abstract

“…Aircraft configurations are available for each mission profile. Fixed-wing aircraft pull the air backwards at high speed by turning the propeller in the longitudinal axis direction (Coban et al , 2020). The resulting high-speed airflow passes under the wings and creates a pressure difference.…”

Section: Introductionmentioning

confidence: 99%

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

“…The reason for this can be shown as the poor performance of traditional tuning methods when the systems are not linear [16]. With the development of metaheuristic algorithms, their use in controller design has become widespread and has become more efficient to find the optimum PID parameter values [17].…”

Section: Introductionmentioning

confidence: 99%

Metaheuristic algorithm-based cascade PID controller design for fixed wing unmanned aerial vehicle

DURMAZ,

CİCİ,

SARIKAYA

et al. 2023

European Mechanical Science

View full text Add to dashboard Cite

In this study, the nonlinear model of the longitudinal motion and altitude of a fixed-wing unmanned aerial vehicle with assured geometrical features and aerodynamic parameters is linearized under certain conditions. A cascade Proportional Integral Differential Controller is designed on the linear model. The controller coefficients that applied to the model of the UAV were optimized with an artificial intelligence technique, which is based on a metaheuristic search algorithm. The four different controller gains in the system are optimized using four different objective functions. Controller performances were tested in simulation environment for unit step input responses., Considering the longitudinal dynamics of the aircraft, among the ITAE, ISE, MSE, and IAE fitness functions, IAE can be shown as the optimum result for altitude control.

show abstract

Improving Autonomous Performance of a Passive Morphing Fixed Wing UAV

Cited by 8 publications

References 11 publications

Stochastic optimal tuning for flight control system of morphing arm octorotor

Stochastic optimal tuning for flight control system of morphing arm octorotor

Simultaneous arm morphing quadcopter and autonomous flight system design

Metaheuristic algorithm-based cascade PID controller design for fixed wing unmanned aerial vehicle

Contact Info

Product

Resources

About