Fuzzy control of a landing gear system with oleo-pneumatic shock absorber to reduce aircraft vibrations by landing impacts

Arık, Ahmet Enes; Bilgiç, Boğaç

doi:10.1108/aeat-01-2022-0028

Cited by 6 publications

(3 citation statements)

References 20 publications

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“…The key feature of the scout UAV is long endurance, which needs to reduce weight as much as possible [4][5]. Sometimes, there is a pair of assistant landing gears for the longendurance UAV which mainly helps the UAV to take off and then drop at a certain height above ground [6]. The departure device for the assistant landing gear is mainly used to disengage the assistant landing gear from the UAV during the take-off stage, which executes the departure action according to the height information acquired by the sensor.…”

Section: Introduction Uav (Unmanned Aerial Vehiclementioning

confidence: 99%

Departure Device Design With Dual Redundancy for the Assistant Landing Gear of Long-endurance UAV

Yang,

Wang,

Liang

2024

J. Phys.: Conf. Ser.

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In modern wars and regional conflicts, in order to reduce casualties, more and more unmanned equipment and weapons are utilized. Among them, the UAV is the new favorite in the sky. Application fields of the military UAV are wide and varied. It is found to be used for intelligence reconnaissance, battlefield surveillance, as well as strikes. As for the scout UAV, long endurance is of utmost importance. There is no denying that less weight can result in longer endurance. A departure device for the assistant landing gear of a long-endurance UAV is designed in this paper. The system constitution and working principles are introduced in the beginning. Then, detailed system designs are presented, including the hardware design, software design, and other parts of the departure device. Several static and dynamic experiments are conducted to prove its feasibility. At last, the conclusion part summarizes its applications.

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Section: Introduction Uav (Unmanned Aerial Vehiclementioning

confidence: 99%

Departure Device Design With Dual Redundancy for the Assistant Landing Gear of Long-endurance UAV

Yang,

Wang,

Liang

2024

J. Phys.: Conf. Ser.

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“…However, this control strategy lacked the robustness needed to control the landing gear system in the presence of uncertainties. In [15], a landing gear system with an oleo-pneumatic shock absorber was also controlled using the fuzzy control strategy. However, the authors completely ignored the effect of signal and measurement delays in their simulation, thereby limiting the abilities of the control strategy.…”

Section: Introductionmentioning

confidence: 99%

Linear Quadratic Gaussian Control of a 6-DOF Aircraft Landing Gear

Nkemdirim,

Alzayed,

Chaoui

2023

Energies

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The suspension system of the aircraft, provided by the landing gear, is a crucial part of landing, take-off, and taxiing. It is important that this suspension system not only adequately supports the airframe of the aircraft but also provides a comfortable, seamless ride for the passengers. However, the landing gear is usually riddled with issues, such as landing vibrations that affect passenger comfort and cause damage to the aircraft’s airframe. To reduce these vibrations, this paper proposes the use of a Linear Quadratic Gaussian (LQG) controller to control a 6-DOF aircraft landing gear. The LQG controller is an optimal controller that combines the Linear Quadratic Regulator (LQR) controller with the Kalman filter to compute the system’s control signals and estimate the system’s states. In this paper, the state space model of the 6-DOF landing gear is derived, and the mathematical model of the LQG controller is calculated. The controller’s performance is then tested via MATLAB/Simulink and compared with an equally simple control strategy, the PID controller. The results obtained from the testing process indicate that the LQG controller surpasses the PID controller in reducing landing vibrations, maintaining the aircraft’s airframe, and providing passenger comfort.

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“…However, this control strategy lacked the robustness needed to control the landing gear system in the presence of uncertainties. In [43], a landing gear system with an oleo-pneumatic shock absorber was also controlled using the fuzzy control strategy. However, the authors did not take the effect of signal and measurement delays into account in their simulation thereby limiting the abilities of the control strategy.…”

Section: -Dof Aircraft Landing Gearmentioning

confidence: 99%

Linear Quadratic Optimal Control of Nonlinear Dynamic Systems

Nkemdirim

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Despite the progress made in the field of control engineering, there are still significant challenges involved in the control of nonlinear dynamic systems. This thesis presents a novel approach to addressing these challenges by leveraging the simplicity of linear optimal quadratic controllers to achieve efficient control of nonlinear dynamic systems that are otherwise considered too difficult to control. In this thesis, three nonlinear dynamic applications are presented: the 3-DOF helicopter, the 6-DOF aircraft landing gear, and the loudspeaker system. These systems face various challenges, including unstable dynamics, landing vibrations, intermodulation distortions, and under-actuation. As such, the Linear Quadratic Regulator (LQR) controller is proposed to control the 3-DOF Helicopter, the Linear Quadratic Gaussian (LQG) controller is proposed for the control of the 6-DOF aircraft landing gear, and both the LQR and the LQG controllers are proposed to control the loudspeaker system.The LQR controller computes the control signals of the systems while the LQG controller acts as a state estimator. The state-space model of each nonlinear dynamic system is derived, and then, the mathematical models of the optimal control strategies are calculated. The control strategies are also tested under various conditions and compared with an equally simple control strategy, the PID controller. To better evaluate the execution and the performance of the LQR and LQG control strategies, two quantitative tracking performance metrics are presented; i) the integral of the tracking errors, and ii) the integral of the control signals of the system. The results obtained affirm the robustness and competence of the proposed control strategies.

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Fuzzy control of a landing gear system with oleo-pneumatic shock absorber to reduce aircraft vibrations by landing impacts

Cited by 6 publications

References 20 publications

Departure Device Design With Dual Redundancy for the Assistant Landing Gear of Long-endurance UAV

Departure Device Design With Dual Redundancy for the Assistant Landing Gear of Long-endurance UAV

Linear Quadratic Gaussian Control of a 6-DOF Aircraft Landing Gear

Linear Quadratic Optimal Control of Nonlinear Dynamic Systems

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