Flutter suppression for the Active Flexible Wing - Control system design and experimental validation

Waszak, Martin R.; Srinathkumar, S.

doi:10.2514/6.1992-2097

Cited by 10 publications

(5 citation statements)

References 9 publications

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“…The relative prominence of the flutter mode among the various transfer functions was strongly influenced by the variation in location of a critical, lowly damped zero relative to the pole that became unstable (see Ref. 12 for a discussion of the impact of the critical zero upon controller design). The analysis indicated that all of the wing accelerometers, with appropriate high-frequency filtering, were viable candidates for feedback.…”

Section: Flutter and Input/output Characteristicsmentioning

confidence: 99%

Design and multifunction tests of a frequency domain-based active flutter suppression system

Adams

Christhilf²

1995

Journal of Aircraft

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This article describes the process of analysis, design, digital implementation, and subsonic testing of an active controls flutter suppression system for a full-span, free-to-roll, wind-tunnel model of an advanced fighter concept. A frequency domain representation of the plant was employed, and a robust multiinput/multioutput controller was generated by using optimization techniques to maximize singular value robustness criteria and insensitivity to uncertainty in the flutter frequency. During testing in a fixed-in-roll configuration, simultaneous suppression of both symmetric and antisymmetric flutter was successfully demonstrated. For a free-to-roll configuration, symmetric flutter was suppressed to the limit of the tunnel test envelope. During aggressive rolling maneuvers above the open-loop flutter boundary, simultaneous flutter suppression and maneuver load control were demonstrated. Finally, the flutter suppression controller was reoptimized during the test using combined experimental and analytical frequency domain data, resulting in improved stability robustness. The reoptimization, accomplished overnight, shows the potential, with a much faster computer, to apply the design procedure to a tuningtype adaptive active flutter suppression controller.

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Section: Flutter and Input/output Characteristicsmentioning

confidence: 99%

Design and multifunction tests of a frequency domain-based active flutter suppression system

Adams

Christhilf²

1995

Journal of Aircraft

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“…Classical control theory was readily adaptable for early attempts to provide stability augmentation for flight vehicles. Some applications conducted on classic aircrafts emerged from this stage, such as the B-52 Controls Configured Vehicle [13], the wind tunnel model of the Active Flexible Wing program [4,5], and the YF-17 scaled model [6]. Some objects might have a multi-input/multi-output (MIMO) characteristic, but their controllers were still treated as single-input/singleoutput (SISO).…”

Section: Introductionmentioning

confidence: 99%

Application of output feedback sliding mode control to active flutter suppression of two-dimensional airfoil

Yang

Song

et al. 2010

Sci. China Technol. Sci.

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The effectiveness of the sliding mode control (SMC) method for active flutter suppression (AFS) and the issues concerning control system discretization and control input constraints were studied using a typical two-dimensional airfoil. The airfoil has a trailing-edge flap for flutter control. The aeroelastic system involves a two-degrees-of-freedom motion (pitch and plunge), and the equations were constructed by utilizing quasi-steady aerodynamic forces. The control system, designed by the output feedback SMC method, was incorporated to suppress the pitch-plunge flutter. Meanwhile, the system discretization and the flap deflection constraints were implemented. Then, a classical Runge-Kutta (RK) algorithm was utilized for numerical calculations. The results indicated that the close-loop system with the SMC system could be stable at a speed above the flutter boundary. However, when the flap deflection limits are reached, the close-loop system with the simple discretized control system loses control. Furthermore, control compensation developed by theoretical analysis was proposed to make the system stable again. The parameter perturbations and the time delay effects were also discussed in this paper. aeroelasticity, flutter, airfoil, sliding mode control, output feedback control Citation:Yang C, Song C, Wu Z G, et al. Application of output feedback sliding mode control to active flutter suppression of two-dimensional airfoil. Sci

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“…Over the past several decades, a large number of control strategies had been developed for active flutter suppression using classical and modern control theory, such as PID control, 2 pole-assignment method, 3 LQR and LQG control, 4 H ∞ control, µ-synthesis, 5 neural-network control, 6 etc.…”

Section: Introductionmentioning

confidence: 99%

Active Flutter Suppression Combining the Receptance Method and Flutter Margin

Cooper²

2016

57th AIAA/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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Active flutter suppression is used to prevent flutter throughout the flight envelope by supplying active control forces in response to vehicle motions. In recent years, studies have been conducted on active flutter suppression using the receptance method. The advantage of the receptance method is that the feedback control gains are purely based upon measured receptances, without any need to evaluate or know the mass, damping, and stiffness matrices of the system. However, determination of the desired closed-loop poles is a unsolved problem. The goal of this work is to determine the pole-assignment in the receptance method, enabling the extension of flutter boundaries by combining the receptance method with the flutter margin technique. The design of an output feedback control for a multi-degree-of-freedom uniform wing numerical model with a trailing-edge control surface is demonstrated. Numerical results show that the presented approach can effectively extend the flutter boundary without the usual difficulties of pole-assignment.

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Flutter suppression for the Active Flexible Wing - Control system design and experimental validation

Cited by 10 publications

References 9 publications

Design and multifunction tests of a frequency domain-based active flutter suppression system

Design and multifunction tests of a frequency domain-based active flutter suppression system

Application of output feedback sliding mode control to active flutter suppression of two-dimensional airfoil

Active Flutter Suppression Combining the Receptance Method and Flutter Margin

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