Robust Finite-Time Continuous Control of an Unsteady Aeroelastic System

Lee, Keum W.; Singh, Sahjendra N.

doi:10.2514/1.g003087

Cited by 11 publications

(6 citation statements)

References 28 publications

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“…Remark 8. According to the function properties of (19), we can obtain that Γ φ iM ð φ i Þ are bounded, i.e., |Γ 6…”

Section: Resultsmentioning

confidence: 99%

“…In [18], an adaptive robust control scheme with input constraints was proposed for MEMS to improve the antidisturbance ability. Thereafter, an adaptive supertwisting continuous control method [19] and adaptive sliding mode controller with neural network observer [20] were developed for multi-input and multioutput aeroelastic system with unsteady aerodynamics in the presence of uncertainty and gust loads. Recently, an effective function estimator using the interval type-2 and type-3 fuzzy logic system has been extensively studied for adaptive control.…”

Section: Introductionmentioning

confidence: 99%

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Prescribed Performance Adaptive Control for a Nonlinear Aeroelastic System with Input Constraint

Gao

Zhang

et al. 2022

International Journal of Aerospace Engineering

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A constrained prescribed performance compensation controller is proposed for a nonlinear aeroelastic system in the presence of wind gust, system uncertainties, and input saturation. To deal with the effects of the nonsmooth saturation nonlinearity, an approximate saturation function is introduced into the controller design, which can smoothly approximate the real saturation with arbitrarily prescribed precision. Specifically, by designing the prescribed performance function, a fixed-time control framework is designed to ensure that the closed-loop system has the prescribed tracking performance. The designed control algorithm can not only compensate the adverse effect caused by disturbances and uncertainties but also restrain the excessive amplitude of control input. Finally, the stability analysis shows that all the signals in the closed-loop system are semiglobally uniformly ultimately bounded via the Lyapunov stability analysis method, and simulation results are presented to demonstrate the feasibility and effectiveness of the proposed method.

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“…Remark 8. According to the function properties of (19), we can obtain that Γ φ iM ð φ i Þ are bounded, i.e., |Γ 6…”

Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Prescribed Performance Adaptive Control for a Nonlinear Aeroelastic System with Input Constraint

Gao

Zhang

et al. 2022

International Journal of Aerospace Engineering

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“…In the definition of the structural matrices, non-linearity is assumed in the torsional (pitch) and transverse displacement (plunge) of the structural stiffness parameters. Various models are adopted in literature, one of the common approaches describing polynomial nonlinearity of stiffness parameters [18]:…”

Section: Geometric Non-linearitiesmentioning

confidence: 99%

Optimal Control for Distributed Aeroelastic Morphing Structure with Uncertainties and Imperfections

Mkhoyan,

Wang,

De Breuker

2024

AIAA SCITECH 2024 Forum

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This research takes a further step towards the development of an autonomous aeroservoelastic wing concept with distributed flaps. The wing demonstrator, developed within the TU Delft SmartX project, aims to demonstrate in-flight performance optimization and multi-objective control using an over-actuated wing design. To address the challenges posed by the aeroelastic system's nonlinearities and uncertainties, this paper employs an optimal control method relying on solving the State-Dependent Riccati Equation (SDRE). Geometrical nonlinearities, introduced in the form of plunge and torsion stiffness, make the system state-dependent and unsuitable for linear control methods. Additionally, a backlash model is incorporated to represent the uncertainty of the actuation system. The control strategy is implemented in a multi-objective manner to perform maneuver and gust load alleviation while accounting for the nonlinearities and uncertainties using the SDRE control. Firstly, a numerical sample case is investigated involving a state-dependent and highly non-linear canard aircraft configuration, to assess the ability of the SDRE control method. Then, in a numerical experiment, the effectiveness of the control strategy is evaluated through the nonlinear aeroelastic model. Evaluations are made on the practicality of the control approach, laying a foundation for future static and dynamic wind tunnel experiments with the SmartX-Neo demonstrator.

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“…LCOs are an important problem and normally associated with flutter. They can severely jeopardize aircraft performance and dramatically affect flight safety . If the flutter is not suppressed in time, it will lead to catastrophic structural failure.…”

Section: Introductionmentioning

confidence: 99%

“…In recent years, some researchers have considered the design of controllers using a single trailing edge flap . A robust supertwisting continuous control law for finite time control of an aeroelastic system in the presence of uncertainty and gust loads was presented in . An adaptive sliding mode fault tolerant control was derived by using an on‐line updating law to estimate the bound of the actuator fault .…”

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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Robust Finite-Time Continuous Control of an Unsteady Aeroelastic System

Cited by 11 publications

References 28 publications

Prescribed Performance Adaptive Control for a Nonlinear Aeroelastic System with Input Constraint

Prescribed Performance Adaptive Control for a Nonlinear Aeroelastic System with Input Constraint

Optimal Control for Distributed Aeroelastic Morphing Structure with Uncertainties and Imperfections

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

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