Linear Parameter-varying Fault-tolerant Control of Morphing Aircraft with Actuator Failures

doi:10.12382/bgxb.2025.0045

Abstract

Abstract:

A sliding mode fault-tolerant control method based on polytopic linear parameter-varying (LPV) model is proposed to address the matched disturbances and actuator multiplicative failures of morphing aircraft during the flight process.An LPV model of morphing aircraft is established based on the longitudinal nonlinear dynamics model of morphing aircraft undergoing wingspan deformation.The LPV model is transformed into a polytopic form,which can convert the infinite-dimensional linear matrix inequality (LMI) problem into a finite-dimensional LMI problem.In order to ensure the stability and robustness of the morphing aircraft when the system actuator malfunctions,a gain-scheduled fault-tolerant control algorithm is proposed by selecting a suitable sliding mode surface and designing a sliding mode fault-tolerant control law.The fault-tolerant control algorithm is applied to the morphing aircraft for simulation verification.The simulated results show that the fault-tolerant control algorithm can be used to ensure the stability and anti-interference ability of the closed-loop system when the actuator fails.

Key words: morphing aircraft, linear parameter-varying model, linear matrix inequality, sliding mode control, fault-tolerant control

CLC Number:

V249.121

FAN Xu’en, CAI Guangbin, WU Tong, XIAO Yongqiang, SHANG Yiming. Linear Parameter-varying Fault-tolerant Control of Morphing Aircraft with Actuator Failures[J]. Acta Armamentarii, 2025, 46(8): 250045-.

Figures/Tables 9

Fig.1 Morphing aircraft in the process of wingspan deformation

Fig.2 Wingspan deformation command

Fig.3 Open-loop response of nonlinear/LPV model for morphing aircraft(ξ:0→1)

Fig.4 Open-loop zero-pole response of morphing aircraft

Fig.5 LPV-based sliding mode fault-tolerant control scheme for morphing aircraft

Fig.6 Closed-loop responses of morphing aircraft for w(t)=[0.01sin(0.1πt) 0.01sin(0.1πt)]T

Fig.7 Control inputs of morphing aircraft for w(t)=[0.01sin(0.1πt) 0.01sin(0.1πt)]T

Fig.8 Closed-loop responses of morphing aircraft for w(t)=[0.03sin(0.1πt) 0.03sin(0.1πt)]T

Fig.9 Control inputs of morphing aircraft for w(t)=[0.03sin(0.1πt) 0.03sin(0.1πt)]T

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