Attitude and altitude control for a fixed wing UAV applied to photogrammetry

Hernandez, J.; González-Hernández, I.; Lozano, Rogelio

doi:10.1109/icuas.2019.8798035

Cited by 4 publications

(3 citation statements)

References 10 publications

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“…Unmanned aerial vehicles can be categorized into two basic categories: rotary-wing and fixed-wing [4]. Due to their capacity to fly long distances and carry heavy payloads, fixed-wing UAVs are currently gaining popularity and are employed for a variety of tasks [5]. Yet, fixed-wing UAVs quickly lose their stability when disturbances arise (weather or wind gusts).…”

Section: Introductionmentioning

confidence: 99%

Feedback Controller for Longitudinal Stability of Cessna182 Fixed-Wing UAVs

Phunpeng,

Wanna,

Khaengkarn

et al. 2023

Adv. sci. technol. eng. syst. j.

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Unmanned aerial vehicles (UAVs) are becoming increasingly popular for both civil and military applications. Unmanned aerial vehicles can be categorized into two categories: rotary-wing and fixed-wing. Due to its capacity to fly long distances and carry substantial payloads, fixed-wing UAVs are gaining popularity and are currently utilized for various tasks. However, when confronted with disturbances such as weather or wind gusts, fixedwing UAVs can rapidly lose stability, leading to a loss of lift and stalling. Consequently, it is vital to ensure the stability of fixed-wing UAVs. For the longitudinal stability management of a fixed wing unmanned aerial vehicle, the design and modeling of a feedback controller, including a PI controller, PID controller, and Fuzzy logic controller, are discussed in this article. MATLAB/SIMULINK©2021 will be used to design the control system and compare the response of each controller during the simulation. The controller's response to various input formats will indicate its capacity to regulate the system's behavior. Our results indicate that the fuzzy logic controller was superior to the PI and PID controllers at controlling the system's response according to the desired or input behavior.

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Section: Introductionmentioning

confidence: 99%

Feedback Controller for Longitudinal Stability of Cessna182 Fixed-Wing UAVs

Phunpeng,

Wanna,

Khaengkarn

et al. 2023

Adv. sci. technol. eng. syst. j.

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“…They considered the accuracy and reliability of flight parameters measured by modern sensors and pointed out that for a particular WIG craft, the concept of flight control needed careful consideration as well as the control algorithms required special research and design. In addition, a majority of studies of flight control for conventional small fixed-wing aircraft focus on attitude and altitude control in the presence of external disturbance caused by wind, failing to give sufficient consideration to the influence of ground effect [12][13][14][15][16][17][18]. Akyurek et al [13] developed an autopilot system containing an inner loop and outer loop for small fixed-wing aircraft.…”

Section: Introductionmentioning

confidence: 99%

“…Ahsan et al [12] compared PID controller with phase lead compensator and found that phase lead 3 International Journal of Aerospace Engineering compensator had a faster transient response and smaller overshoots. Hernandez and González-Hernández [15] compared the PID controller with the nonlinear controller by simulation. They found that in the use of stabilizing UAV's attitude and altitude, only a linear control system was enough for the roll angle control, while in the cases of the other two attitude control and altitude control, PID had better results.…”

Section: Introductionmentioning

confidence: 99%

High Precision Height Control for Wing-in-Ground Crafts

Mei

Shan

et al. 2022

International Journal of Aerospace Engineering

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The wing-in-ground effect craft (WIG craft) is a kind of vehicle that flies close to the ground to achieve a flight with low aerodynamic drag and high lift. A robust and precise height control system is essential to ensure small WIG crafts fly safely in ground effect. In this paper, the performance of different high precision height control systems based on PID controllers is investigated numerically with different altitude disturbances. The results show that a control system that operates throttle, elevators, and flaps to control the altitude of the aircraft (TPF control system) results in the minimum overshoot, undershoot, rising tine, and settling time recovering from a disturbed altitude, with fluctuation in pitch angle. Compared to the TPF control system, even though the control system that operates throttle and flaps (TF control system) has a longer settling time and a higher overshoot, it has a smaller oscillation in pitch angle during a disturbed altitude. In addition, operating the throttle helps reduce the change of flight velocity during altitude disturbance. Furthermore, simulation results based on the TPF control system, show that the ground effect has little influence on the performance of control systems.

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