Robust control of a three degrees of freedom aeroelastic model using an intelligent observer

Prabhu, L.; Srinivas, J.

doi:10.1109/race.2015.7097251

Cited by 3 publications

(1 citation statement)

References 9 publications

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“…In other words, all of the system states are assumed to be measurable. To the authors' knowledge, there are few investigations on the observer‐controller for aeroelastic system . A LQG control strategy using a sliding mode observer (SMO) was proposed and the performance was demonstrated by simulation in .…”

Section: Introductionmentioning

confidence: 99%

Sliding Mode Observer Controller Design for a Two Dimensional Aeroelastic System with Gust Load

Yuan¹,

Qiu²,

Wang³

2018

Asian Journal of Control

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The aim of this paper is to develop state estimation and sliding mode control schemes for the vibration suppression of an underactuated wing aeroelastic system in the presence of a gust load disturbance. Ignoring structural elastic deformation and using the concentrated elastic system (spring) to simulate the overall elastic deformation, this aeroelastic model consists of a straight wing and spring system, describing flap and pitch freedoms. The corresponding dynamic motion equation is established using the Lagrange method, and the gust is modeled as a typical "1-cosine" gust. The aerodynamic lift and moment on the wing are computed by strip theory. The open loop system exhibits the limit cycle oscillations (LCOs) at a certain freestream velocity. The objective is to design a control system for suppressing the LCOs. For the purpose of control, a single trailing-edge control surface is used. It is assumed that only the pitch angle is measured and the remaining state variables needed for full state feedback are estimated by the designed observer. Then an integral sliding surface is put forward on the estimation space; a new continuous reaching law is proposed to reduce the chattering phenomena. The finite-time reachability of the predesigned sliding surface is proved and guaranteed by the designed sliding mode control law. The sufficient condition for the asymptotic stability of the closed-loop system composed of the sliding mode dynamics and the error dynamical system is derived in terms of linear matrix inequality (LMI). The effectiveness of the proposed strategy is finally demonstrated by simulation results.

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Section: Introductionmentioning

confidence: 99%

Sliding Mode Observer Controller Design for a Two Dimensional Aeroelastic System with Gust Load

Yuan¹,

Qiu²,

Wang³

2018

Asian Journal of Control

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Adaptive Control of Aircraft Wing Oscillations with Stiffness and Damping Nonlinearities in Pitching Mode

Prabhu

Srinivas

2018

Advances in Intelligent Systems and Computing

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Disturbance Observer-Based Backstepping Terminal Sliding Mode Aeroelastic Control of Airfoils

Liu,

Yang,

Zhang

et al. 2024

Aerospace

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This paper studies aeroelastic control for a two-dimensional airfoil–flap system with unknown gust disturbances and model uncertainties. Open loop limit cycle oscillation (LCO) happens at the post-flutter speed. The structural stiffness and quasi-steady and unsteady aerodynamic loads of the aeroelastic system are represented by nonlinear models. To robustly suppress aeroelastic vibration within a finite time, a backstepping terminal sliding-mode control (BTSMC) is proposed. In addition, a learning rate (LR) is incorporated into the BTSMC to adjust how fast the aeroelastic response converges to zero. In order to overcome the fact that the BTSMC design is dependent on prior knowledge, a nonlinear disturbance observer (DO) is designed to estimate the variable observable disturbances. The closed-loop aeroelastic control system has proven to be globally asymptotically stable and converges within a finite time using Lyapunov theory. Simulation results of an aeroelastic two-dimensional airfoil with both trailing-edge (TE) and leading-edge (LE) control surfaces show that the proposed DO-BTSMC is effective for flutter suppression, even when subjected to gusts and parameter uncertainties.

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Robust control of a three degrees of freedom aeroelastic model using an intelligent observer

Cited by 3 publications

References 9 publications

Sliding Mode Observer Controller Design for a Two Dimensional Aeroelastic System with Gust Load

Sliding Mode Observer Controller Design for a Two Dimensional Aeroelastic System with Gust Load

Adaptive Control of Aircraft Wing Oscillations with Stiffness and Damping Nonlinearities in Pitching Mode

Disturbance Observer-Based Backstepping Terminal Sliding Mode Aeroelastic Control of Airfoils

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