Adaptive backstepping fast terminal sliding mode controller design for ducted fan engine of thrust-vectored aircraft

Asl, Sayed Bagher Fazeli; Moosapour, Seyyed Sajjad

doi:10.1016/j.ast.2017.10.001

Cited by 57 publications

(12 citation statements)

References 18 publications

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“…In order to improve the robustness of backstepping control, earlier research suggests combining Sliding Mode Control (SMC) with backstepping [8,10,[14][15][16][17]. The main idea of this combination is to use a SMC virtual control input to compensate for the uncertain term ε bs .…”

Section: A Backstepping Sliding Mode Controlmentioning

confidence: 99%

“…Only the upper bound of this lumped uncertainty term is needed by conventional first-order SMC methods [11], while the upper bounds of the uncertainty derivatives are required by higher-order SMC methods [12,13]. These requirements on knowledge of the bounds can further be removed by various Adaptive Sliding Mode Control (ASMC) methods [10,14].…”

Section: Introductionmentioning

confidence: 99%

“…There have been continuous efforts in combining backstepping techniques with SMC to preserve the merits of both methods [8,10,[14][15][16][17]. A second-order SMC is combined with ABS for feedback linearizable single-input/output (SISO) nonlinear systems that can be transformed into the parametric-pure feedback form and the parametric-strict feedback form in [8], where an SMC virtual control is included at the last step of the ABS design to improve robustness.…”

Section: Introductionmentioning

confidence: 99%

“…In order to remove the pre-knowledge of the uncertainty bound, backstepping is hybridized with an ASMC method for a spacecraft attitude control problem in [10]. Adaptive fast terminal SMC with nonlinear sliding surface is incorporated into the backstepping framework for controlling the ducted fan engine of a thrust-vectored aircraft in [14]. In spite of the various SMC designs, the main idea of the combination is consistent in the above methods, that for the recursive steps encounter uncertainties, SMC virtual controls are incorporated into the baseline backstepping virtual control designs.…”

Section: Introductionmentioning

confidence: 99%

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Incremental Backstepping Sliding Mode Fault-Tolerant Flight Control

Wang

Kampen

2019

AIAA Scitech 2019 Forum

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Fault-tolerant flight control has the potential of improving the aircraft survivability in real life. This paper proposes an Incremental Backstepping Sliding Mode Control (IBSMC) framework for multi-input/output nonlinear strict-feedback systems considering model uncertainties, sudden faults, and external disturbances. This approach is a hybridization of the Sliding Mode Control (SMC) and a reformulated Incremental Backstepping (IBS). By virtue of the benefits contributed by both SMC and IBS, theoretical analyses prove IBSMC has less model dependency and enhanced robustness as compared to backstepping and backstepping hybridized with SMC (BSMC). When applied to an aircraft fault-tolerant control problem, numerical simulations demonstrate IBSMC can passively tolerate a wider range of model uncertainties, sudden actuator faults, and sudden structural damages as compared to backstepping and BSMC, using smooth control inputs with lower gains.

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Section: A Backstepping Sliding Mode Controlmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Incremental Backstepping Sliding Mode Fault-Tolerant Flight Control

Wang

Kampen

2019

AIAA Scitech 2019 Forum

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“…However, the existence of a PID controller may weaken the antiinterference ability of the system. While SMC has been regarded as the most efficient method for disturbance rejection and robustness properties in mechatronic system [16][17][18], and it has been applied in PMSM systems successfully.…”

Section: Introductionmentioning

confidence: 99%

Novel fast terminal sliding mode controller with current constraint for permanent-magnet synchronous motor

Yao¹,

Kong²,

Ding³

2021

Turkish Journal of Electrical Engineering and Computer Sciences

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Under the noncascade structure, the balance between q-axis current constraint and dynamic performance in permanent-magnet synchronous motor system has become a critical problem. On the one hand, large transient current is required to provide high torque to achieve fast dynamic performance. On the other hand, current constraint becomes a state constraint problem, instead of governing q-axis reference current in the cascade structure directly. Aiming at this issue, a novel fast terminal sliding mode control (FTSMC)-based controller with current constraint is developed in this paper. The novelty of this scheme is related to the proposed penalty function based on interior point method, which is established in control action directly. Unlike ordinary solutions, the suggested solution combined with sliding mode variable can achieve current constraint of q-axis without scarifying dynamic performance. Furthermore, by adopting the FTSMC-type surface and new reaching law, the proposed implementation guarantees high performance with significant reduction of chattering phenomenon and has fast convergence characteristics. Then, the stability proof of the whole closed-loop system by employing the Lyapunov method is given in detail. Finally, series of simulations are provided to evaluate the performance of the presented FTSMC-type controller, in terms of current constraint, dynamic performance, and chattering reduction.

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A multilayer neural‐network‐based fault estimation and fault tolerant control scheme for uncertain system

Akhtar,

Naqvi,

Hamayun

et al. 2024

Intl J Robust & Nonlinear

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This work introduces a new actuator fault estimation approach coupled with a fault‐tolerant control (FTC) strategy for uncertain systems in an output feedback framework. The proposed method involves constructing a Multi‐Layer Neural Network (MLNN) observer‐based fault estimation unit to accurately predict system states and potential faults in the actuator channel. An online control allocation (CA) scheme is then developed, utilizing the derived estimates to actively reconfigure the virtual control signals among the healthy redundant actuators in the event of actuator malfunction. Furthermore, an adaptive neural network‐based output integral sliding mode control scheme is designed based on the virtual control. This integration enhances the overall system's robustness and significantly reduces the chattering effect. The stability analysis of the proposed fault estimations scheme is initially performed using MLNN structure, followed by a comprehensive closed‐loop stability analysis to establish the stability of the entire system. Finally, the effectiveness of the proposed method is validated on a nonlinear six‐degree‐of‐freedom model of multirotor unmanned aerial vehicle aircraft. Numerical simulations under different fault and failure scenarios validate the efficacy of the proposed method. The comparative analysis of the proposed scheme is conducted with the static output feedback control allocations and adaptive allocation strategy. This analysis focuses on evaluating performance using metrics such as root mean square error and mean square deviation, particularly in the presence of faults and failures. The results demonstrate the superior performance of the proposed scheme in fault/failure conditions.

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Adaptive backstepping fast terminal sliding mode controller design for ducted fan engine of thrust-vectored aircraft

Cited by 57 publications

References 18 publications

Incremental Backstepping Sliding Mode Fault-Tolerant Flight Control

Incremental Backstepping Sliding Mode Fault-Tolerant Flight Control

Novel fast terminal sliding mode controller with current constraint for permanent-magnet synchronous motor

A multilayer neural‐network‐based fault estimation and fault tolerant control scheme for uncertain system

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