Reconfiguration control method for non-redundant actuator faults on unmanned aerial vehicle

Boche, Adèle; Farges, Jean‐Loup; Plinval, Henry de

doi:10.1177/0954410019841745

Cited by 2 publications

(3 citation statements)

References 10 publications

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“…e control reconfiguration technology for the control system in the presence of faults is a key way to realize the soft redundancy [13]. It can be divided into active reconfiguration and passive reconfiguration, based on Fault Detection and Identification (FDI) and FDI-free reconfiguration methods [14][15][16]. As one of the most popular control reconfiguration methods, the area of adaptive control is attracting increasing attention [17][18][19], and researchers have proposed many advanced methods combined with adaptive control [20][21][22].…”

Section: Introductionmentioning

confidence: 99%

Simple Adaptive Control‐Based Reconfiguration Design of Cabin Pressure Control System

et al. 2021

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The Cabin Pressure Control System (CPCS) is an essential part of the aviation environmental control system that ensures aircraft structure and flight crew safety. However, the CPCS usually has potential faults of sensors and actuators. To this end, a Simple Adaptive Control- (SAC-) based reconfiguration method is proposed to compensate for the above adverse effects. Some good pressure control performance of CPCS can be achieved by the basic pressure controller when the system is in normal operation. A parallel feedforward compensator is designed to guarantee the closed-loop system’s stability and the almost strictly positive realness of the augmented system. Thus, the simple adaptive controller can be utilized for the CPCS. In particular, the reconfiguration system can update the control law online when the fault occurs without the system identification process. The reference model is obtained by mathematical model linearization after considering the mechanical characteristics of the CPCS. Extensive simulations under various typical fault scenarios are carried out throughout the entire flight envelope of the aircraft from take-off to landing. Simulation results validate the robustness and reconfiguration control capability of the proposed method.

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Section: Introductionmentioning

confidence: 99%

Simple Adaptive Control‐Based Reconfiguration Design of Cabin Pressure Control System

et al. 2021

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“…[1][2][3] Actuator fault is investigated in several recent literature. [4][5][6] Shin et al 4 introduced a reconfigurable flight control system using adaptive sliding mode control (SMC) for actuator fault. In Boche et al, 5 an indirect discrete continuous FTC scheme is applied to the longitudinal dynamics of a fixed-wing unmanned aerial vehicle in the presence of elevon fault.…”

Section: Introductionmentioning

confidence: 99%

“…[4][5][6] Shin et al 4 introduced a reconfigurable flight control system using adaptive sliding mode control (SMC) for actuator fault. In Boche et al, 5 an indirect discrete continuous FTC scheme is applied to the longitudinal dynamics of a fixed-wing unmanned aerial vehicle in the presence of elevon fault. Roshanravan et al 6 also designed a fault tolerant autopilot for a nonlinear pitch-axis model of an air vehicle subject to actuator loss of effectiveness.…”

Section: Introductionmentioning

confidence: 99%

Nonlinear robust adaptive control of an airplane with structural damage

Asadi

Ahmadi

2020

Proceedings of the Institution of Mechanical Engineers, Part G:

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This article investigates the design of a novel nonlinear robust adaptive control architecture to stabilize and control an airplane in the presence of left-wing damage. Damage effect is modeled by considering the sudden mass and inertia changes, center of gravity, and aerodynamic variations. The novel nonlinear control algorithm applies a state predictor as well as the error between the real damaged dynamics and a virtual model based on the nominal aircraft dynamics in the control loop of the adaptive strategy. The projection operator is used for the purpose of robustness of the adaptive control algorithm. The stability of the proposed nonlinear robust adaptive controller is demonstrated applying the Lyapunov stability theory. The performance of the proposed controller is compared with two previous successful algorithms, which are implemented on the Generic Transport Model airplane to accommodate wing damage. Numerical simulations demonstrate the effectiveness and advantages of the proposed robust adaptive algorithm regarding two other algorithms of adaptive sliding mode and L 1 adaptive control.

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Reconfiguration control method for non-redundant actuator faults on unmanned aerial vehicle

Cited by 2 publications

References 10 publications

Simple Adaptive Control‐Based Reconfiguration Design of Cabin Pressure Control System

Simple Adaptive Control‐Based Reconfiguration Design of Cabin Pressure Control System

Nonlinear robust adaptive control of an airplane with structural damage

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