Comparison of SDRE and SMC control approaches for flutter suppression in a nonlinear wing section

El-hami, M.; Narab, Mahdi Fatehi

doi:10.1109/acc.2012.6314699

Cited by 15 publications

(16 citation statements)

References 5 publications

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“…The simulation is based on the dynamic model given in (1). The dynamic parameters utilized in the simulation are summarized in Table 2 and were obtained from [18]. The control gains , , 0 , and were manually selected as described in Table 1 (Figures 8 and 9).…”

Section: Resultsmentioning

confidence: 99%

A Sliding Mode LCO Regulation Strategy for Dual-Parallel Underactuated UAV Systems Using Synthetic Jet Actuators

Ramos-Pedroza

MacKunis

Reyhanoglu

2015

International Journal of Aerospace Engineering

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A sliding mode control-(SMC-) based limit cycle oscillation (LCO) regulation method is presented, which achieves asymptotic LCO suppression for UAVs using synthetic jet actuators (SJAs). With a focus on applications involving small UAVs with limited onboard computational resources, the controller is designed with a simplistic structure, requiring no adaptive laws, function approximators, or complex calculations in the control loop. The control law is rigorously proven to achieve asymptotic regulation of both pitching and plunging displacements for a class of systems in a dual-parallel underactuated form, where a single scalar control signal simultaneously affects two states. Since dual-parallel underactuated systems cannot be expressed in a strict feedback or cascade form, standard backstepping-based control techniques cannot be applied. This difficulty is mitigated through careful algebraic manipulation in the regulation error system development, along with innovative design of the sliding surface. A detailed model of the UAV LCO dynamics is utilized, and a rigorous analysis is provided to prove asymptotic regulation of the pitching and plunging displacements. Numerical simulation results are provided to demonstrate the performance of the control law.

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Section: Resultsmentioning

confidence: 99%

A Sliding Mode LCO Regulation Strategy for Dual-Parallel Underactuated UAV Systems Using Synthetic Jet Actuators

Ramos-Pedroza

MacKunis

Reyhanoglu

2015

International Journal of Aerospace Engineering

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“…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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“…Wang et al [4,5] proposed a full-state feedforward/feedback controller with a high-gain observer considering a class of aeroelastic systems with an unmodeled nonlinearity and external disturbance; they also designed a continuous robust controller to suppress the aeroelastic vibrations of a nonlinear wing-section model. Elhami and Narab [9] used the SMC method to suppress airfoil flutter, and a comparison between the SMC method and the State-Dependent Riccati Equation approach was carried out. Zhang et al [7] designed a partial state feedback continuous adaptive controller in order to suppress the aeroelastic vibrations of the wing section model.…”

Section: Introductionmentioning

confidence: 99%

Fault‐Tolerant Control for Flutter of Airfoil Subject to Input Saturation

Luo

Gao

Cai

2016

Asian Journal of Control

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In this paper, a fault tolerant control is studied for a two-dimensional airfoil with input saturation and actuator fault. The dynamic equation of airfoil flutter is firstly established, in which the cubic hard spring nonlinearity of pitch stiffness is considered. Then, an adaptive sliding mode fault tolerant control is derived by using an on-line updating law to estimate the bound of the actuator fault such that no information about the fault is needed. Furthermore, an auxiliary design system is introduced to resolve actuator saturation in control. Next, Lyapunov stability analysis is carried out to prove that the system is asymptotically stable. Finally, the effectiveness of the proposed controller is verified through numerical simulations.Simulation results indicate that the adaptive sliding mode fault tolerant controller is effective in suppressing airfoil flutter under partial loss of actuator effectiveness performance and input saturation.

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Comparison of SDRE and SMC control approaches for flutter suppression in a nonlinear wing section

Cited by 15 publications

References 5 publications

A Sliding Mode LCO Regulation Strategy for Dual-Parallel Underactuated UAV Systems Using Synthetic Jet Actuators

A Sliding Mode LCO Regulation Strategy for Dual-Parallel Underactuated UAV Systems Using Synthetic Jet Actuators

Saturated RISE Tracking Control of Store-Induced Limit Cycle Oscillations

Fault‐Tolerant Control for Flutter of Airfoil Subject to Input Saturation

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