Efficient nonlinear reduced-order modeling for synthetic-jet-based control at high angle of attack

Li, Wencheng; Jin, Dongping; Zhao, Yonghui

doi:10.1016/j.ast.2016.11.029

Cited by 18 publications

(8 citation statements)

References 24 publications

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“…Therefore, it can be used for active flow control at a high AoA [27]. Here, an optimized cavity shape with a better performance proposed in our previous work is employed, as shown in Figure 2b [28].…”

Section: Modeling For Roll Moment For Sjamentioning

confidence: 99%

Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack

Wang

Huang

et al. 2021

Applied Sciences

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Flow separation and dynamic stall occurring at a high angle of attack will lead to difficulty in control and maneuverability for morphing aircraft. This study proposes a novel active flow control technology using a synthetic jet actuator for the roll motion of morphing aircraft. With the help of the computational fluid dynamics method and vortex lattice method, the roll control model of morphing aircraft undergoing large shape change at a high angle of attack is established. In this model, both the array of the actuator with an optimized cavity shape and morphing span, which are subject to the input saturation constraint, are used to mimic the conventional control surface. Integrated flight control based on the sliding mode control method is designed to ensure the desired closed-loop asymptotic stability, wherein the radial basis function neural network is employed to provide the compensation induced by the input saturation constraint. To demonstrate the effectiveness of the control scheme, various control strategies for different combinations of input are proposed to maintain the roll motion. The numerical results show that the designed control law could track the target signal well, which suggests that the virtual control surface is an effective tool for maintaining the high flight performance of morphing aircraft.

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Section: Modeling For Roll Moment For Sjamentioning

confidence: 99%

Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack

Wang

Huang

et al. 2021

Applied Sciences

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“…Glaz, Liu and Friedmann [23] developed a Kriging-based recurrent ROM that accounts for flow unsteadiness, time-history effects, and nonlinearities at a constant or varying Mach number to predict unsteady lift, moment, and drag coefficients of a rotating airfoil. The Kriging-based surrogate model was utilized by Li, Jin, and Zhou [24] to obtain unsteady and nonlinear A-ROM for active flow-based synthetic jet control. Liu et al [25] also developed a Kriging-based ROM to predict aeroelastic responses (pitch angle and plunge displacement) of a NACA 64A010 airfoil in transonic flow with varying Mach numbers.…”

Section: Introductionmentioning

confidence: 99%

State consistence of data-driven reduced order models for parametric aeroelastic analysis

et al. 2021

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This paper investigates the state consistence of parametric data-driven reduced order models (ROMs) in a state-space form obtained by various system identification methods, including autoregressive exogenous (ARX) and subspace identification (N4SID), for aeroelastic analysis in varying flight conditions. The target flight envelop is first partitioned into discrete grid points, on each of which an aerodynamic ROM is constructed using system identification to capture the dependence of the generalized aerodynamic force on the generalized displacement of structural modes. High-fidelity aeroelastic modal perturbation simulations are used to generate the ROM training and verification data. Aerodynamic ROMs not on the grid point are obtained by interpolating those at neighboring grid points. Through a thorough analysis of the model coefficients and pole migration, it is found that only the ARX-based aerodynamic ROM preserves the state consistence, and hence, allowing direct interpolation of system matrices at the non-grid point and rapid aerodynamic ROM database development in the entire flight parameter space. In contrast, N4SID-based ROM destroys the state consistence and yields physically meaningless results when ROMs are interpolated. The origin of the difference in the state consistence caused by both methods is also discussed. The interpolated ARX aerodynamic ROMs coupled with the structural ROM for parametric aeroelastic analysis exhibit excellent agreement with the high fidelity full order model (mostly <5% relative error) and salient computational efficiency.

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“…As another promising AFC method, SJ has considerable application potential on controlling static and dynamic stall of rotor airfoil. [16][17][18] Different from deformation strategies, SJ could delay or prevent the formation of dynamic stall vortex of an oscillatory airfoil by introducing periodic disturbance into the separated flow, at the same time, it does not change the aerodynamic shape of airfoil, which is helpful to maintain a low level of radar area of rotor airfoil. 19 Hassan et al numerically analyzed the effectiveness of SJ on dynamic stall suppression for VR-7 airfoil, 20 and the benefits of SJ for improving the aerodynamic characteristics of airfoil with onset of the dynamic stall were well validated.…”

Section: Introductionmentioning

confidence: 99%

New combinational active control strategy for improving aerodynamic characteristics of airfoil and rotor

Zhao

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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In order to improve the aerodynamic characteristics of rotor, a new active flow control strategy by combining a synthetic jet actuator and a variable droop leading-edge or a trailing-edge flap has been proposed. Their control effects are numerically investigated by computational fluid dynamics (CFD) method. The validated results indicate that variable droop leading-edge and synthetic jet can suppress the formation of dynamic stall vortex and delay flow separation over rotor airfoil. Compared with the baseline state, Cdmax and Cmmax are significantly reduced. Furthermore, parametric analyses on dynamic stall control of airfoil by the combinational method are conducted, and it indicates that the aerodynamic characteristics of the oscillating rotor airfoil can be significantly improved when the non-dimensional frequency ( k*) of variable droop leading-edge is about 1.0. At last, simulations are conducted for the flow control of rotor by the combinational method. The numerical results indicate that large droop angle of variable droop leading-edge can better reduce the torque coefficient of rotor and the trailing-edge flap has the capability of increasing the thrust of rotor. Also, the synthetic jet could further improve the aerodynamic characteristics of rotor.

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Efficient nonlinear reduced-order modeling for synthetic-jet-based control at high angle of attack

Cited by 18 publications

References 24 publications

Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack

Roll Control of Morphing Aircraft with Synthetic Jet Actuators at a High Angle of Attack

State consistence of data-driven reduced order models for parametric aeroelastic analysis

New combinational active control strategy for improving aerodynamic characteristics of airfoil and rotor

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