Super-twisting sliding mode control for aircraft at high angle of attack based on finite-time extended state observer

Liu, Junjie; Sun, Mingwei; Chen, Zengqiang; Sun, Qinglin

doi:10.1007/s11071-020-05481-1

Cited by 52 publications

(29 citation statements)

References 38 publications

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“…The relation in the formula (18) must be satisfied for termed reachability condition of DSMC systems, which means that the system trajectory of (1) is driven towards the sliding surface (12) and then remains on it thereafter. It is easy to give the expression (18), but it possesses some conservativeness. For the slowly time-varying unmatched disturbance, we will further give an adaptive gain with less conservativeness.…”

Section: Design Of Adaptive Reaching Lawmentioning

confidence: 99%

“…Proof The designed adaptive switching gain (19) will be first testified to fulfill the inequality (18). In view of ( 9), it is demonstrated that…”

Section: Design Of Adaptive Reaching Lawmentioning

confidence: 99%

“…Inevitably, the lumped disturbances including parameter uncertainties, external disturbances and unmodeled dynamics in practical systems may not satisfy the matching condition [20]. Concerning this problem, a lot of methods have been studied, such as linear matrix inequality (LMI) based approach [6], integral sliding mode control [3], extended state observer based control [29], disturbance observer based control (DOBC) [5,18].…”

Section: Introductionmentioning

confidence: 99%

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Reduced-order disturbance observer-based adaptive reaching law control for discretized MIMO systems with unmatched uncertainties

et al. 2021

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In this paper, an adaptive discrete-time sliding mode control based on reduced-order disturbance observer is proposed for discretized multi-input multi-output systems subjected to unmatching condition. By using the designed discrete reduced-order disturbance observer, a new sliding surface is constructed to counteract the unmatched uncertainties. Then, to guarantee a smaller width of the quasi sliding mode domain, an adaptive reaching law is developed, whose switching gain is adaptively tuned to prevent overestimation of disturbance on the premise of ensuring the reaching condition of sliding surface; meanwhile, the ranges of the quasi sliding mode band and attractiveness region are deduced. The proposed control algorithm has low computational complexity and needs no information about the upper bound of unmatched disturbance. The simulations on the control of a bank-to-turn missile demonstrate that the proposed method can effectively reject unmatched disturbance, and provide higher accuracy in comparison with traditional methods. Keywords Discrete-time sliding mode control • Adaptive reaching law • Reduced-order disturbance observer • Unmatched disturbance • Multi-input multi-output system

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Section: Design Of Adaptive Reaching Lawmentioning

confidence: 99%

“…Proof The designed adaptive switching gain (19) will be first testified to fulfill the inequality (18). In view of ( 9), it is demonstrated that…”

Section: Design Of Adaptive Reaching Lawmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Reduced-order disturbance observer-based adaptive reaching law control for discretized MIMO systems with unmatched uncertainties

et al. 2021

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“…where 𝜅 is the modulation gain, which is usually greater than the parametric value of interference and uncertainty, but higher modulation gain will cause undesired chattering in the system, which is not feasible in practical engineering. Therefore, the adaptive modulation gain function (38) is designed here to control the magnitude of the adaptive gain 𝜅.…”

Section: ) Adaptive Ism Control Law Design For Outer Loopmentioning

confidence: 99%

Hybird Nonlinear Control for Fighter With Center of Gravity Perturbation and Aerodynamic Parameter Uncertainty

et al. 2021

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In this paper, a hybrid nonlinear control scheme combines nonlinear dynamic inversion (NDI) and adaptive sliding mode (ASM) control is proposed for high angle of attack fighter system with center of gravity perturbation and aerodynamic parameter uncertainty. By introducing the affine nonlinear model of inner loop angular velocity with center of gravity perturbation, an adaptive sliding mode control scheme based on the online estimation of radial basis function (RBF) neural network is designed, which can reduce the dynamic inversion error of NDI control and rapidly compensate the multi-coupled channel oscillation. The aerodynamic force and moment coefficients are estimated via the iterative weighted least squares (IRLS) method. The outer loop integral sliding mode (ISM) NDI controller is designed, which can be robust to disturbances and mismatched uncertainties through adjusting adaptive gain, and the rudder yaw chattering caused by the uncertainty of aerodynamic parameters is reduced simultaneously. The Lyapunov stability theory and Barbarat lemma prove the stability of the designed control scheme, and the effectiveness of the hybrid nonlinear control scheme is verified based on F-16 model.

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“…Liu et al proposed a finite-time decoupling control strategy for aircraft with thrust vectors at high angles of attack maneuver. They used a three-channel decoupling control scheme based on finite-time extended state observer to realize the high angle of attack maneuver (Liu et al , 2020).…”

Section: Introductionmentioning

confidence: 99%

Integrated design of fault-tolerant control for flight control systems using observer and fuzzy logic

Unal

2021

AEAT

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Purpose Fault detection, isolation and reconfiguration of the flight control system is an important problem to obtain healthy flight. This paper aims to propose an integrated approach for aircraft fault-tolerant control. Design/methodology/approach The integrated structure includes a Kalman filter to obtain without noise, a full order observer for sensor fault detection, a GOS (generalized observer scheme) for sensor fault isolation and a fuzzy controller to reconfigure of the healthy sensor. This combination is simulated using the state space model of a lateral flight control system in case of disturbance and under sensor fault scenario. Findings Using a dedicated observer scheme, the detection and time of sensor fault are correct, but the sensor fault isolation is evaluated incorrectly while the faulty sensor is isolated correctly using GOS. The simulation results show that the suggested approach works affectively for sensor faults with disturbance. Originality/value This paper proposes an integrated approach for aircraft fault-tolerant control. Under this framework, three units are designed, one is Kalman filter for filtering and the other is GOS for sensor fault isolation and another is fuzzy logic for reconfiguration. An integrated approach is sensitive to faults that have disturbances. The simulation results show the proposed integrated approach can be used for any linear system.

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Super-twisting sliding mode control for aircraft at high angle of attack based on finite-time extended state observer

Cited by 52 publications

References 38 publications

Reduced-order disturbance observer-based adaptive reaching law control for discretized MIMO systems with unmatched uncertainties

Reduced-order disturbance observer-based adaptive reaching law control for discretized MIMO systems with unmatched uncertainties

Hybird Nonlinear Control for Fighter With Center of Gravity Perturbation and Aerodynamic Parameter Uncertainty

Integrated design of fault-tolerant control for flight control systems using observer and fuzzy logic

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