Design of active flutter suppression and wind-tunnel tests of a wing model involving a control delay

Huang, Rui; Qian, Wenmin; Hu, Haiyan; Zhao, Youqun

doi:10.1016/j.jfluidstructs.2015.03.014

Cited by 37 publications

(17 citation statements)

References 21 publications

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“…Previous studies have mainly focused on a 2D aeroelastic system, with few cases looking at three-dimensional (3D) aeroelastic models. For example, (Huang et al, 2012;Huang et al, 2015b) presented numerical and experimental studies on the active flutter suppression (AFS) of a 3D wing model involving a control delay. A high-dimensional multiple-actuated-wing was established in their work as a test case to validate the control method.…”

Section: Introductionmentioning

confidence: 99%

“…Generally, aero-servo-elastic studies have used low-fidelity linear aerodynamic models, including lifting surface theory (Yuan et al, 2004), piston theory (Xu et al, 2014), quasi-steady aerodynamics (Zhao, 2009(Zhao, , 2011, and the doublet-lattice method (Huang et al, 2012;Huang et al, 2015b). The assumption of linear aerodynamics is adequate to treat subsonic and supersonic flow regimes .…”

Section: Introductionmentioning

confidence: 99%

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Computational fluid dynamics-based transonic flutter suppression with control delay

Zhou

Ronch

et al. 2016

Journal of Fluids and Structures

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This work investigates the effects of control input time delay on closed-loop transonic computational aeroelastic analysis. Control input time delays are becoming critical as the demand for high frequency control actions is increasing. The flow in transonic conditions exhibits strong nonlinearities which require accurate physical modelling techniques, in turn resulting in large dimensional systems that are computationally costly to solve. A unified framework is demonstrated for the robust and efficient generation of reduced order models. Once generated, the reduced order model is employed for the flutter boundary search, and excellent agreement with the large order coupled model is demonstrated. The aero-servo-elastic reduced order model is then exploited to design a feedback control law, which is implemented in the fully coupled computational fluid/structural dynamics solver. As expected, the controller effectiveness is found to degrade for increasing time delay, up to a critical value where the controller fails to suppress flutter. It is shown that a controller for a time-delay system may be designed using the same aero-servo-elastic reduced order model, incurring in no extra costs or complications. The new controller is found to achieve excellent flutter suppression characteristics. The aero-servo-elastic reduced order model may also be used to identify, for a given feedback controller, the critical value of control input time delay at which the closed-loop aero-servo-elastic system loses its stability. The test cases are for a two-dimensional pitch-plunge aerofoil section and the AGARD 445.6 wing modified with a trailing-edge control surface.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Computational fluid dynamics-based transonic flutter suppression with control delay

Zhou

Ronch

et al. 2016

Journal of Fluids and Structures

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“…Due to the time delay, when unsynchronized control force is applied to a structure, it may result in degradation in the control efficiency and instability of the control system. Among the studies on active flutter suppression, only few of them have addressed the effect of time delays on the stability of controlled aeroelastic systems (Huang, Qian, Hu, & Zhao, 2015;Singh, 2015;Zhao, 2011). Huang et al (2015) presented a new optimal control law to suppress the flutter with an input time delay in the control loop and the delayed controller was digitally implemented and tested for the three-dimensional wing model in NH-2 subsonic wind-tunnel.…”

Section: Introductionmentioning

confidence: 99%

“…Among the studies on active flutter suppression, only few of them have addressed the effect of time delays on the stability of controlled aeroelastic systems (Huang, Qian, Hu, & Zhao, 2015;Singh, 2015;Zhao, 2011). Huang et al (2015) presented a new optimal control law to suppress the flutter with an input time delay in the control loop and the delayed controller was digitally implemented and tested for the three-dimensional wing model in NH-2 subsonic wind-tunnel. Singh (2015) considered a single time delay in the control loop and presented flutter boundary extension by partial pole placement in an aeroelastic system to suppress airfoil flutter.…”

Section: Introductionmentioning

confidence: 99%

“…Therefore, compared with (Amoozgar, 2013;Mardanpour et al, 2014;Mazidi et al, 2013) previous studies, our research is of great significance. (ii) In order to reveal the negative effect of the conventional control on the stability of aeroelastic system (Cassaro & Battipede, 2015;Huang et al, 2015;Singh, 2015;Wang et al, 2012;Zhang et al, 2013;Zhao, 2009Zhao, , 2011 and consider the influence of faults, time delay, input saturation, time-varying parameter uncertainties and external disturbances, this paper focuses on the design of finite-time H 1 adaptive fault-tolerant controller for flutter of wing with propulsion system. The sensor and actuator faults are both considered in the controller design.…”

Section: Introductionmentioning

confidence: 99%

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Finite-time fault-tolerant control for flutter of wing

Gao

Cai

Nan

2016

Control Engineering Practice

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Aeroelastic analysis and flutter control of wings and panels: A review

Chai

Gao

Ankay

et al. 2021

Int Journal of Mech Sys Dyn

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Flutter is a self-excited vibration under the interaction of the inertial force, aerodynamic force, and elastic force of the structure. After the flutter occurs, the aircraft structures will exhibit limit cycle oscillation, which will cause catastrophic accidents or fatigue damage to the structures. Therefore, it is of great theoretical and practical significance to study the aeroelastic characteristics and flutter control for improving the aeroelastic stability of aircraft structures. This paper reviews the recent advances in aeroelastic analysis and flutter control of wings and panel structures. The mechanism of aeroelastic flutter of wings and panels is presented. The research methods of aeroelastic flutter for different structures developed in recent years are briefly summarized. Various control strategies including the linear and nonlinear control algorithms as well as the active flutter control results of wings and panels are presented. Finally, the paper ends with conclusions, which highlight challenges of the development in aeroelastic analysis and flutter control, and provide a brief outlook on the future investigations. This study aims to present a comprehensive understanding of aeroelastic analysis and flutter control. It can also provide guidance on the design of new wings and panel structures for improving their aeroelastic stability.

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Design of active flutter suppression and wind-tunnel tests of a wing model involving a control delay

Cited by 37 publications

References 21 publications

Computational fluid dynamics-based transonic flutter suppression with control delay

Computational fluid dynamics-based transonic flutter suppression with control delay

Finite-time fault-tolerant control for flutter of wing

Aeroelastic analysis and flutter control of wings and panels: A review

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