Aerodynamic Design and Characterization of a Quad Tilt-Wing UAV via Wind Tunnel Tests

Çetinsoy, Ertuğrul; Hançer, Cevdet; Öner, Kaan Taha; Sırımoğlu, Efe; Ünel, Mustafa

doi:10.1061/(asce)as.1943-5525.0000161

Cited by 20 publications

(11 citation statements)

References 14 publications

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“…Remark The lift and drag coefficients required to compute the wing forces in Equation , W l d , are obtained via nonlinear regression using the real data generated from wind‐tunnel tests (see previous study). In the controller design, these forces will be cancelled directly, and in the rest of the development, it will be assumed that this cancellation is already performed.…”

Section: Controller Designmentioning

confidence: 99%

“…The characteristics that make SUAVI a novel quad tilt‐wing UAV and its advantages over existing designs can be found in 1 study . Sabanci University Unmanned Aerial Vehicle was previously designed, manufactured, and flight tested by Unel et al, and earlier research results have been published about the aerodynamic and mechanical design, prototyping, control system design, and flight tests . However, in those studies, the effects of wing‐angle variations, component failures, and unexpected damages on system uncertainty were not investigated and the controller was not tested against these adverse conditions.…”

Section: Introductionmentioning

confidence: 99%

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Nonlinear hierarchical control of a quad tilt‐wing UAV: An adaptive control approach

Yıldız

Ünel

Demirel

2017

Adaptive Control & Signal

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In this paper, a nonlinear hierarchical adaptive control framework is proposed for the control of a quad tilt-wing unmanned aerial vehicle (UAV). An outer loop model reference adaptive controller with robustifying terms creates required forces to be able to move the UAV on a reference trajectory, and an inner loop nonlinear adaptive controller realizes the required attitude angles to achieve these forces. A rigorous stability analysis is provided showing the boundedness of all the signals in this cascaded controller structure. The development and the stability analysis of the controller do not use any linearizations and use the full nonlinear UAV dynamics. The controller is implemented on a high-fidelity nonlinear tilt-wing quadrotor model in the presence of uncertainties, wind disturbances, and measurement noise as well as actuator and structural failures. In this work, in addition to earlier modeling studies, the effect of wing-angle variations, actuator failures, and structural failures and their effect on the center of gravity of the UAV are rigorously and systematically investigated and reflected in the model. Simulation results showing the performance of the proposed controller and a comparison with the fixed controller used in earlier studies are presented in the paper.

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Section: Controller Designmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Nonlinear hierarchical control of a quad tilt‐wing UAV: An adaptive control approach

Yıldız

Ünel

Demirel

2017

Adaptive Control & Signal

Self Cite

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“…Yun et al evaluated the power system's performance by carrying out numerical simulation analyses for the lift efficiency of the lift fan system in hover mode, lift and drag in transition mode, airplane resistance in cruising mode, and aerodynamic coupling of the blade tip turbine and jet engine [15]. Cetinsoy et al compared and analyzed the effects of different airfoil shapes and sizes on the aerodynamic characteristics of tilting wing UAVs; and ultimately determined the structural parameters of the airfoils [16]. Czyba et al used CFD to analyze the lift-drag ratio change in three modes (VTOL, transition conversion, and horizontal flight), and optimized the structural parameters of the wing and propeller installation parameters [17].…”

Section: Introductionmentioning

confidence: 99%

Development of Response Surface Model of Endurance Time and Structural Parameter Optimization for a Tailsitter UAV

Yao

Liu

Han

et al. 2020

Sensors

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This study designed a vertical take-off and landing tailsitter unmanned aerial vehicle (UAV) with a long endurance time. Nine parameters of the tailsitter UAV were investigated. Using a 2k full factorial test, 512 experiments on the nine parameters were conducted at their maximum and minimum values. The time coefficient and air resistance were calculated using the computational fluid dynamics (CFD) method under different parameter combinations. The analysis of variance determined that the specific factors influencing the time coefficient and air resistance were the root chord, wingtip chord, wingspan, and sweep angle. By carrying out a central composite design (CCD) test, 25 sample points of the four particular factors were constructed. The time coefficient and air resistance were simulated under different structural parameter combinations using the CFD method. CFD simulation was verified by carrying out a wind tunnel test, and the results revealed that the aerodynamic coefficient error was less than 5%, while the air resistance error was less than 6%. The response surface methodology (RSM) for the time coefficient and air resistance was established using a genetic aggregation method. A multi-objective genetic algorithm (MOGA) was used to optimize the parameters with regard to the maximum time coefficient and minimum air resistance. The optimal structural parameters were wing root chord length at 315 mm, wingtip chord length at 182 mm, wingspan length at 1198 mm, and sweep angle at 16°. Compared with the original layout and size, the time coefficient of the new design of the tailsitter UAV improved by 19.5%, while the air resistance reduced by 34.78%. The results obtained by this study are significant for the design of tailsitter UAVs.

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“…In recent years, the research on VTOL UAVs is increasingly prosperous with the advancements in automatic control and the increasing popularity of UAV platforms [1]. The problem of transition maneuvers has been studied for different types of UAVs, including a fixed-wing aircraft equipped with a thrust vector engine and lift fan [1][2][3], tiltrotor aircraft [4][5][6][7], tail-sitter aircraft [8,9], ducted-fan VTOL aircraft [10,11], and tilt-wing aircraft [12,13]. A pilot auxiliary control system was designed by Francesco and Mattei [1] for a fixed-wing tiltrotor UAV, and the control logics for different flight states were specified and synthesized through adopting INDI method.…”

Section: Introductionmentioning

confidence: 99%

VTOL UAV Transition Maneuver Using Incremental Nonlinear Dynamic Inversion

Liu

Guo

et al. 2018

International Journal of Aerospace Engineering

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The paper seeks to study the control system design of a novel unmanned aerial vehicle (UAV). The UAV is capable of vertical takeoff and landing (VTOL), transition flight and cruising via the technique of direct force control. The incremental nonlinear dynamic inversion (INDI) approach is adopted for the 6-DOF nonlinear and nonaffine control of the UAV. Based on the INDI control law, a method of two-layer cascaded optimal control allocation is proposed to handle the redundant and coupled control variables. For the weight selection in optimal control allocation, a dynamic weight strategy is proposed. This strategy can adjust the weight of the objective function according to the flight states and mission requirements, thus determining the optimizing direction and ensuring the rationality of the allocation results. Simulation results indicate that the UAV can track the target trajectory accurately and exhibit continuous maneuverability in transition flight.

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Aerodynamic Design and Characterization of a Quad Tilt-Wing UAV via Wind Tunnel Tests

Cited by 20 publications

References 14 publications

Nonlinear hierarchical control of a quad tilt‐wing UAV: An adaptive control approach

Nonlinear hierarchical control of a quad tilt‐wing UAV: An adaptive control approach

Development of Response Surface Model of Endurance Time and Structural Parameter Optimization for a Tailsitter UAV

VTOL UAV Transition Maneuver Using Incremental Nonlinear Dynamic Inversion

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