A cascaded nonlinear fault-tolerant control for fixed-wing aircraft with wing asymmetric damage

Liu, Yu; Liu, Xiaoxiong; Ming, Ruichen; Zhu, Hongyuan; Zhang, Weiguo

doi:10.1016/j.isatra.2022.10.021

Cited by 8 publications

(3 citation statements)

References 31 publications

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“…The HIL flight control experiment platform is made up of joysticks, a ground station, an autopilot, a real-time simulation computer, a simulator, and a visual display software, in which, excluding the joysticks and the real-time simulation computer, the rest of the components are designed and developed independently by our laboratory. 47 The autopilot named DreamBuilder is used for the navigation and control of the UAVs and rotors. It adopts the STM32F429 as the processor and is equipped with a series of communication interfaces, such as RS232 and RS485 ports, an airspeed sensor, an IMU module, a magnetic sensor, a GPS module, and a 900 MHz FM radio.…”

Section: Hil Experimentsmentioning

confidence: 99%

“…The HIL flight control experiment platform is made up of joysticks, a ground station, an autopilot, a real‐time simulation computer, a simulator, and a visual display software, in which, excluding the joysticks and the real‐time simulation computer, the rest of the components are designed and developed independently by our laboratory 47 . The autopilot named DreamBuilder is used for the navigation and control of the UAVs and rotors.…”

Section: Simulation and Analysismentioning

confidence: 99%

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Improved model reference‐based adaptive nonlinear dynamic inversion for fault‐tolerant flight control

Liu

Ming

et al. 2023

Intl J Robust & Nonlinear

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Due to lack of robustness, Nonlinear Dynamic Inversion (NDI) control cannot resist the influence of disturbances. In this paper, an adaptive fault‐tolerant control method, called Improved Model Reference‐based Adaptive NDI (IMR‐ANDI), is proposed and applied to develop a fault‐tolerant flight controller to improve robustness to faults and disturbances. To improve the estimation accuracy, this paper also modified the piecewise‐constant adaptation, which improves the accuracy of adaptive estimation without increasing the sampling frequency. Moreover, a low‐pass filter is introduced to the control law creatively to weaken the disturbance of high‐frequency dynamics to the adaptation, which balances the dynamic performance and robustness as well as prevents the system oscillation. Finally, a fault‐tolerant flight controller is developed based on the IMR‐ANDI and verified under the actuator fault and center of gravity variations. All simulation and hardware‐in‐the‐loop experiment results conform to the theoretical analysis, indicating that the developed IMR‐ANDI fault‐tolerant controller is robust to faults and disturbances and can achieve expected control performance.

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Section: Hil Experimentsmentioning

confidence: 99%

Section: Simulation and Analysismentioning

confidence: 99%

Improved model reference‐based adaptive nonlinear dynamic inversion for fault‐tolerant flight control

Liu

Ming

et al. 2023

Intl J Robust & Nonlinear

Self Cite

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“…The characteristics of aircraft include complex flight environment, strong nonlinearity of the model, and so on. Nonlinear control of aircraft [1][2][3] has always been a hot and challenging problem in the field of control. The tracking control of aircraft track angle [4][5] is a particularly important part of the aircraft control system, which has been widely used in aircraft system design.…”

Section: Introductionmentioning

confidence: 99%

Command Filter AILC for Finite Time Accurate Tracking of Aircraft Track Angle System Based on Fuzzy Logic

Zhang,

Tian,

Gao

et al. 2023

Advances in Mathematical Physics

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In this paper, the longitudinal model of an uncertain aircraft is taken as the research object, and the aircraft path inclination is controlled by controlling the input rudder deflection angle. An adaptive iterative learning control (AILC) scheme is proposed to solve the accurate tracking control problem of the flight path inclination on a finite time interval. The aircraft track angle system is abstractly modeled to obtain a triangular model in the form of strict feedback. For the abstracted strict feedback model, the fuzzy logic is used to approximate the uncertain part of the model. A command filter and an error compensation mechanism are introduced to prevent the computational bloat problem caused by excessive system order, and a convergent series sequence is used to deal with the truncation error caused by the approximation of the fuzzy logic. Based on the Lyapunov stability theorem, all signals of the closed-loop system are bounded on the finite time interval 0 , T , and the output of the system can track the desired trajectory accurately. Finally, the feasibility and effectiveness of the method are verified by MATLAB simulation results.

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Adaptive Control Scheme for Carrier-Based UAVs with Actuator Failure

Xue,

Zou,

Chen

et al. 2024

Lecture Notes in Electrical Engineering

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A cascaded nonlinear fault-tolerant control for fixed-wing aircraft with wing asymmetric damage

Cited by 8 publications

References 31 publications

Improved model reference‐based adaptive nonlinear dynamic inversion for fault‐tolerant flight control

Improved model reference‐based adaptive nonlinear dynamic inversion for fault‐tolerant flight control

Command Filter AILC for Finite Time Accurate Tracking of Aircraft Track Angle System Based on Fuzzy Logic

Adaptive Control Scheme for Carrier-Based UAVs with Actuator Failure

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