Robust adaptive fault-tolerant control of a tandem coaxial ducted fan aircraft with actuator saturation

Wang, Xiaoliang; Chen, Xiang; Najjaran, Homayoun; Xu, Bugong

doi:10.1016/j.cja.2018.03.018

Cited by 26 publications

(8 citation statements)

References 23 publications

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“…The experiments are conducted at the Vehicle Research Center of BIT (Beijing Institute of Technology). There are a variety of SR vehicles 10,11,[38][39][40][41] developed successfully in the laboratory. In our past work, 10 the test model is mounted vertically and reversely on a test bench (0.3 m 3 0.3 m 3 1.2 m) so that the air flows from bottom to top.…”

Section: Methodsmentioning

confidence: 99%

Aerodynamic performance and analysis of a hovering micro-scale shrouded rotor in confined environment

Han

Chen

et al. 2019

Advances in Mechanical Engineering

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The aerodynamic characteristics of open rotor hovering in confined environment are extensively studied, but few papers focus on shrouded rotor. In order to study aerodynamic performance and flowfield characteristics of micro-scale shrouded rotor hovering in confined environment, experimental measurements and computational fluid dynamic simulations are conducted in this article. Three cases of confined planes including ground, ceiling, and wall close to shrouded rotor are studied successively. Another case of no confined planes around shrouded rotor is also researched. Results show that both ground and ceiling improve the aerodynamic performance of shrouded rotor at distance below 1.5 rotor radii with the enhanced figure of merit, while wall plane influences flight stability because of the unbalanced moment. The experimental data reveal that the performance of shrouded rotor in-ground effect is more sensitive than that of shrouded rotor in-ceiling effect. However, for in-ground effect or in-ceiling effect, the performance of shrouded rotor is more sensitive than that of open rotor. Flowfield analysis by computational fluid dynamic shows the confined planes block airflow around shrouded rotor. Tip flow leakage and flow separation occur near shroud lip when shrouded rotor is hovering considerably close to ground or ceiling. Turbulent vortices and fluctuating velocities affect the flight stability of shrouded rotor.

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Section: Methodsmentioning

confidence: 99%

Aerodynamic performance and analysis of a hovering micro-scale shrouded rotor in confined environment

Han

Chen

et al. 2019

Advances in Mechanical Engineering

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“…In previous research, we have done a series of relevant studies on the prototype [ 31 , 32 , 33 , 34 , 35 ]. Through the continuous optimization of the prototype structure and design, the latest prototype with the manipulation is shown in Figure 2 .…”

Section: The Aerodynamic Influence Of Corner Effect On the Prototymentioning

confidence: 99%

Modeling of a Novel Coaxial Ducted Fan Aerial Robot Combined with Corner Environment by Using Artificial Neural Network

Chen

et al. 2020

Sensors

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A novel coaxial ducted fan aerial robot with a manipulator is proposed which can achieve some hover operation tasks in a corner environment, such as switching on and off a wall-attached button on the corner. In order to study the aerodynamic interference between the prototype and the environment when the aerial robot is hovering in the corner environment, a method for the comprehensive modeling of the prototype and corner environment based on the artificial neural network is presented. By using the CFD simulation software, the flow field of the prototype at different positions with the corner effect is analyzed. After determining the input, output and structure of the neural network model, the Adam and gradient descent algorithms are selected as the neural network training algorithms, respectively. In addition, to optimize the initial weights and biases of the neural network model, the genetic algorithm is precisely used. The three-dimensional prediction surfaces generated by the three methods of the neural network, kriging surface and the polynomial fitting are compared. The results show that the neural network has high prediction accuracy, and can be applied to the comprehensive modeling of the prototype and the corner environment.

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“…The main differences between the two FTC strategies are that an adjustable control structure or parameters based on fault detection and diagnosis (FDD) are employed in the AFTC [11,12]. A large number of achievements for FTC have been obtained in the last few decades, including sliding mode FTC [13], model reference adaptive FTC [14], neural adaptive FTC [15,16], fuzzy FTC [17,18], eventtriggered FTC [19,20], back-stepping FTC [21,22], etc. Because of the great advantages in dealing with the high order chain integral system among these methods, the back-stepping control method is widely used in the design of the FTC scheme.…”

Section: Introductionmentioning

confidence: 99%

Back-stepping Fault-tolerant Control for Morphing Aircraft Based on Fixed-time Observer

Liang

Wang

et al. 2021

Int. J. Control Autom. Syst.

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In this paper, the problem of the back-stepping fault-tolerant control (FTC) based on fixed-time observer is addressed for the morphing aircraft with model uncertainties, external disturbances, and actuator faults. First, the longitudinal dynamics for the morphing process are presented, and the control-oriented models subject to undesired malfunctions are established. Second, the fixed-time observer is designed for offering estimations of compound disturbances, including system uncertainties, disturbance, and malfunction information. Especially, the observer errors could converge to zero by the proposed observer within a settling time, which is independent of the system's initial conditions. Then, a back-stepping FTC strategy based on the observations is proposed for the altitude and velocity subsystem, and the stability of the close loop system would be guaranteed by the proposed controller despite the actuator failures. Furthermore, to eliminate the effects of the "explosion of complexity" of the backstepping method, a modified dynamic surface is applied to compute derivatives of virtual laws. Finally, the numerical simulations verify the effectiveness of the proposed control approach.

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Robust adaptive fault-tolerant control of a tandem coaxial ducted fan aircraft with actuator saturation

Cited by 26 publications

References 23 publications

Aerodynamic performance and analysis of a hovering micro-scale shrouded rotor in confined environment

Aerodynamic performance and analysis of a hovering micro-scale shrouded rotor in confined environment

Modeling of a Novel Coaxial Ducted Fan Aerial Robot Combined with Corner Environment by Using Artificial Neural Network

Back-stepping Fault-tolerant Control for Morphing Aircraft Based on Fixed-time Observer

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