Control law design for transonic aeroservoelasticity

Zhang, Weiwei; Ye, Zhengyin

doi:10.1016/j.ast.2006.12.004

Cited by 48 publications

(16 citation statements)

References 35 publications

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“…The relevant parameters are α 0 = 0 • , a = 0, x α = 0.0035, r 2 α = 1.036, ω h /ω α = 0.6539, and ω α = 32.67 rad/s based on NACA0012 airfoil [67]. The flutter boundaries are calculated based on hybrid linear multistep method, and M2 mesh is adopted.…”

Section: Validation Of the Flutter Boundarymentioning

confidence: 99%

The interaction between flutter and buffet in transonic flow

et al. 2015

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This paper presents a kind of nodal-shaped oscillation that is caused by the interaction between flutter and buffet in transonic flow. This response differs from the common limit cycle oscillation that appears in transonic aeroelastic problems. The benchmark active controls technology model with the NACA0012 airfoil is used as the research model. First, both buffet and flutter cases are computed through unsteady Reynolds-averaged Navier-Stokes method and are validated by experimental data. Second, the interaction is found to occur beyond the flutter onset velocity at Mach 0.71. When the pitching angle of a fluttering structure exceeds the buffet onset angle, the highfrequency aerodynamic loads induced by transonic buffet destroy the original flutter model, and then the amplitude of the structure motion decays. When the structural pitching angle is less than the buffet onset angle, the buffet disappears and flutter occurs again. As the process repeats itself, the transonic aeroelastic system displays a nodal-shaped oscillation (divergentdamping-divergent-damping oscillation). Finally, the mechanism of the interaction is discussed by analyzing the energy transportation between the flow and the structure in one cycle of nodal-shaped oscillation, and by observing the variation in the phase-angle difference between the plunging and pitching displacements. In this way, this research provides a new approach to understand flutter suppression.

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Section: Validation Of the Flutter Boundarymentioning

confidence: 99%

The interaction between flutter and buffet in transonic flow

et al. 2015

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“…Several control strategies have been developed to mitigate LCO behavior in an aeroelastic system requiring exact knowledge of the dynamics including linear-quadratic regulator (LQR), 3,17,23 feedback linearization, 12 linear multivariable control on a linear reduced order model, 6,21 and State-Dependent Riccati Equation and sliding mode control approaches. 8 These controllers do not compensate for uncertainties in the aerodynamic and structural models or external disturbances and are restricted to specific flight regimes.…”

Section: Introductionmentioning

confidence: 99%

Saturated RISE Tracking Control of Store-Induced Limit Cycle Oscillations

Bialy

Andrews

Curtis

et al. 2013

AIAA Guidance, Navigation, and Control (GNC) Conference

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This paper presents the development of a saturated robust integral of the sign of the error (RISE) feedback controller for an airfoil section undergoing store-induced limit cycle oscillations. The controller is designed to asymptotically track the airfoil section angle of attack (AoA) in the presence of structural and aerodynamic uncertainties without breaching actuator limits through a smooth saturation function. A Lyapunov-based stability analysis is used to prove global asymptotic tracking of the AoA. Simulation results demonstrate the performance of the developed controller.

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“…21 For the controller design of the aeroservoelastic model, a good deal of work has been done. [22][23][24][25][26] In recent study, a lot of work has been conducted on controller design for WC model (Winged-cone model) and COM (Control-oriented model). 27 WC model is a six-DOF model of HFV without elasticity.…”

Section: Introductionmentioning

confidence: 99%

Aeroservoelastic modeling and analysis of a six-DOF hypersonic flight vehicle

Zong

You

Zeng

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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By using light-weighted material in hypersonic flight vehicle, the vehicle body can be easily deformed. The mutual couplings in aerodynamics, flexible structure and control system will result in aeroservoelasticity problem. Based on the six-DOF geometry of a hypersonic flight vehicle, this paper uses assumed modes method, Shock-Expansion theory and Piston theory to develop the structural elastic model and the aerodynamic model, with actuator incorporated, the open-loop aeroservoelastic model of a six-DOF HFV is established. In open-loop analysis, the response of the elastic coordinates to the tail rudder deflection and the frequency characteristic of the transfer function of the tail rudder deflection to the first elastic coordinate are studied. A high gain feedback controller is designed for the aeroservoelastic model, and closed-loop analysis is conducted based on this model. The simulations show the influence of the elastic motion on the aerodynamic forces and moments.

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Control law design for transonic aeroservoelasticity

Cited by 48 publications

References 35 publications

The interaction between flutter and buffet in transonic flow

The interaction between flutter and buffet in transonic flow

Saturated RISE Tracking Control of Store-Induced Limit Cycle Oscillations

Aeroservoelastic modeling and analysis of a six-DOF hypersonic flight vehicle

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