Performance comparison of two altitude-control algorithms for a fixed-wing UAV

Ahsan, Mansoor; Shafique, Kamran; Mansoor, Asif; Mushtaq, Muddassar

doi:10.1109/ic4.2013.6653744

Cited by 12 publications

(7 citation statements)

References 5 publications

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“…General equation for frequency domain description for phase lead compensator is given by Equation (4) [17];…”

Section: Plant Description When In Loop With Lead Compensatormentioning

confidence: 99%

“…It helps in moving the close loop poles towards the negative half of the s-plane, due to which stability and speed of the system response is optimized. This technique is proven to be fruitful in one of the studies investigated for pitch and altitude control by Ahsan et al [17]. They investigated that by using a PLC, transient response characteristics were improved as compared to PID controller.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

The Implementation and Lateral Control Optimization of a UAV Based on Phase Lead Compensator and Signal Constraint Controller

Loya¹,

Duraid²,

Maqsood³

et al. 2018

ENG

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Unmanned Aero Vehicles (UAV) has become a useful entity for quite a good number of industries and facilities. It is an agile, cost effective and reliable solution for communication, defense, security, delivery, surveillance and surveying etc. However, their reliability is dependent on the resilient and stabilizes performance based on control systems embedded behind the body. Therefore, the UAV is majorly dependent upon controller design and the requirement of particular performance parameters. Nevertheless, in modern technologies there is always a room for improvement. In the similar manner a UAV lateral control system was implemented and researched in this study, which has been optimized using Proportional, Integral and Derivative (PID) controller, phase lead compensator and signal constraint controller. The significance of this study is the optimization of the existing UAV controller plant for improving lateral performance and stability. With this UAV community will benefit from designing robust controls using the optimized method utilized in this paper and moreover this will provide sophisticated control to operate in unpredictable environments. It is observed that results obtained for optimized lateral control dynamics using phase lead compensator (PLC) are efficacious than the simple PID feedback gains. However, for optimizing unwanted signals of lateral velocity, yaw rate, and yaw angle modes, PLC were integrated with PID to achieve dynamical stability.

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“…General equation for frequency domain description for phase lead compensator is given by Equation (4) [17];…”

Section: Plant Description When In Loop With Lead Compensatormentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

The Implementation and Lateral Control Optimization of a UAV Based on Phase Lead Compensator and Signal Constraint Controller

Loya¹,

Duraid²,

Maqsood³

et al. 2018

ENG

View full text Add to dashboard Cite

show abstract

“…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%

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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“…e fixed-wing UAVs are inevitable and useful in many fields [1]. Especially, in the military, they show an indispensable position in the modern battle fields with their advantages of strong penetration, strong mobility, and good concealment [2].…”

Section: Introductionmentioning

confidence: 99%

LSTM-Based Output-Constrained Adaptive Fault-Tolerant Control for Fixed-Wing UAV with High Dynamic Disturbances and Actuator Faults

Chang

Rong

Chen

et al. 2021

Mathematical Problems in Engineering

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The unknown disturbances and the changing uncertainties bring difficulties for designing a stable attitude controller for UAV. In this paper, a novel adaptive fault-tolerant attitude control approach is designed based on the long short-term memory (LSTM) network for the fixed-wing UAV subject to the high dynamic disturbances and actuator faults. Firstly, the high dynamic disturbances can be compensated by the adaptive laws. Meanwhile, the actuator faults can be handled by the proposed adaptive fault-tolerant control (AFTC) scheme. Moreover, the LSTM network is introduced to approximate the unknown and time-accumulating nonlinearities. With the introduction of the one-to-one nonlinear mapping (NM), the output constraints in the control system can be guaranteed. Additionally, it can be demonstrated that the boundness of all the signals can be assured. At last, numerical simulation results are provided to illustrate the effectiveness of the proposed method.

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Performance comparison of two altitude-control algorithms for a fixed-wing UAV

Cited by 12 publications

References 5 publications

The Implementation and Lateral Control Optimization of a UAV Based on Phase Lead Compensator and Signal Constraint Controller

The Implementation and Lateral Control Optimization of a UAV Based on Phase Lead Compensator and Signal Constraint Controller

High Precision Height Control for Wing-in-Ground Crafts

LSTM-Based Output-Constrained Adaptive Fault-Tolerant Control for Fixed-Wing UAV with High Dynamic Disturbances and Actuator Faults

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