Stability Evaluation of a Fixed-Wing Unmanned Aerial Vehicle with Morphing Wingtip

Oktay, Tugrul; Eraslan, Yüksel

doi:10.30518/jav.1073417

Cited by 4 publications

(6 citation statements)

References 23 publications

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“…In this article, the morphing application on ZANKA-I fixed-wing UAV refers to an alteration of its wingtip dihedral angle, between 0 70 degrees, by means of folding from a 100 mm spanwise distance from the wingtips, as illustrated in Figure 2, where dihedral angle is represented as Γ. Geometrically, higher values of wingtip dihedral angle result in smaller wing span (m), b, wing area (m 2 ), S, and wing aspect ratio, AR, as might be expected. Furthermore, the effective dihedral angle, effective diherdal angle (EDA), of the entire wing alters, which can be calculated from equations (3) and (4) for multi-dihedral wings, where г is dihedral angle in degrees, f is unitless moment fraction and η is dihedral-break station in percent wing-span location (Oktay and Eraslan, 2022): …”

Section: Unmanned Aerial Vehicle Flight Dynamics and Flight Control S...mentioning

confidence: 99%

Autonomous flight performance optimization of fixed-wing unmanned aerial vehicle with morphing wingtip

Oktay,

Eraslan

2024

AEAT

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Purpose The purpose of this paper is to improve autonomous flight performance of a fixed-wing unmanned aerial vehicle (UAV) via simultaneous morphing wingtip and control system design conducted with optimization, computational fluid dynamics (CFD) and machine learning approaches. Design/methodology/approach The main wing of the UAV is redesigned with morphing wingtips capable of dihedral angle alteration by means of folding. Aircraft dynamic model is derived as equations depending only on wingtip dihedral angle via Nonlinear Least Squares regression machine learning algorithm. Data for the regression analyses are obtained by numerical (i.e. CFD) and analytical approaches. Simultaneous perturbation stochastic approximation (SPSA) is incorporated into the design process to determine the optimal wingtip dihedral angle and proportional-integral-derivative (PID) coefficients of the control system that maximizes autonomous flight performance. The performance is defined in terms of trajectory tracking quality parameters of rise time, settling time and overshoot. Obtained optimal design parameters are applied in flight simulations to test both longitudinal and lateral reference trajectory tracking. Findings Longitudinal and lateral autonomous flight performances of the UAV are improved by redesigning the main wing with morphing wingtips and simultaneous estimation of PID coefficients and wingtip dihedral angle with SPSA optimization. Originality/value This paper originally discusses the simultaneous design of innovative morphing wingtip and UAV flight control system for autonomous flight performance improvement. The proposed simultaneous design idea is conducted with the SPSA optimization and a machine learning algorithm as a novel approach.

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Section: Unmanned Aerial Vehicle Flight Dynamics and Flight Control S...mentioning

confidence: 99%

Autonomous flight performance optimization of fixed-wing unmanned aerial vehicle with morphing wingtip

Oktay,

Eraslan

2024

AEAT

Self Cite

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“…The update velocity and the location of DPSO are given by equations ( 11) and (12), respectively. In the MVFSA, the initial particle is distributed by equation (13), and the random probability of acceptance P r is defined using the Boltzmann-Gibbs distribution in equation (14). Considering the high-dimensional and discrete character of the topology structure for MLFANN, the topological optimization is divided into two parts: the weights and biases of the neural network are optimized using the MSSA, and the number of hidden layers and the number of neurons per hidden layer are optimized using DPSO-MVFSA.…”

Section: Surrogate Modelmentioning

confidence: 99%

Aerodynamic optimization method of intake grille of active clearance control system for turbines based on modified social spider algorithm (MSSA)

Xie,

Zhang,

Shi

et al. 2024

Advances in Mechanical Engineering

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During the operation of an active clearance control (ACC) system of a turbine, the aerodynamic performance of the intake grille indirectly influences its control. To improve the performance, an aerodynamic optimization method is proposed, consisting of parameterization, an optimization algorithm, and a fitness evaluation. During parameterization, its geometry is represented by seven geometric variables. A modified social spider algorithm is used as the optimization algorithm. To evaluate the aerodynamic performance of the grille, a special fitness function is adopted, obtained using an adaptive topological multi-layer feedforward artificial neural network. To verify the feasibility of this method, experiments and numerical calculations are carried out on the original and optimized intake grilles. The results show that the average intake flow rate and average total pressure recovery coefficient of the optimized grille have increased by 17.3% and 4.9%, respectively.

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“…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.…”

Section: Introductionmentioning

confidence: 99%

“…In fixed-wing UAVs, morphing is accomplished by changing the wing plan shapes (Oktay and Eraslan, 2022) and in rotary-wing UAVs, it is usually done by changing arm lengths. Coban et al.…”

Section: Introductionmentioning

confidence: 99%

Stochastic optimal tuning for flight control system of morphing arm octorotor

Kose

2024

AEAT

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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.

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Stability Evaluation of a Fixed-Wing Unmanned Aerial Vehicle with Morphing Wingtip

Abstract: Autopilots are frequently used on UAVs with the purpose of guiding the vehicle without necessity for pilot assistance. This autonomous control performance is a considerable issue for UAVs and dramatically relates with shape of the main

Cited by 4 publications

References 23 publications

Autonomous flight performance optimization of fixed-wing unmanned aerial vehicle with morphing wingtip

Autonomous flight performance optimization of fixed-wing unmanned aerial vehicle with morphing wingtip

Aerodynamic optimization method of intake grille of active clearance control system for turbines based on modified social spider algorithm (MSSA)

Stochastic optimal tuning for flight control system of morphing arm octorotor

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