Robust aeroelastic control of two-dimensional supersonic flapped wing systems

Na, S. S.; Librescu, Liviu; Marzocca, Pier; Yoon, Gwon Chan; Rubillo, Christina; Bong, Kwang Sub

doi:10.1007/s00707-006-0419-3

Cited by 11 publications

(7 citation statements)

References 8 publications

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“…7 depicts the A performance comparison of the two models is produced in terms of the pitching response based on only the plunging displacement feedback, which simulates a hostile environment. It can be seen that the sliding mode observer yields better performance with regard to the estimation of the aeroelastic pitching response than the Kalman filter [4,5]. In Fig.…”

Section: Resultsmentioning

confidence: 92%

“…Furthermore, beyond the flutter speed, the aeroelastic response increases as time unfolds. Here, the flutter speed has been determined from the aeroelastic response and via the harmonic balance method [4][5][6]. The dynamic response in the time histories in Fig.…”

Section: Resultsmentioning

confidence: 99%

“…Marzocca et al [6] implemented a combined linear and nonlinear proportional and velocity control scheme in conjunction with a flap; they revealed the possible expansion of the flutter boundary and lower response amplitude in the post-flutter range. Na et al [4] applied the LQG methodology using an observer to suppress flutter in a 2D flapped wing system and discussed the performance of a robust control strategy. Among the several candidate control techniques that have been developed, sliding mode control (SMC) [11,12] has been selected.…”

Section: Introductionmentioning

confidence: 99%

“…Due to the possibly limited number of available states that are measured through sensors, a state estimator is required. In this context, a Sliding Mode Observer (SMO) will be implemented [4,5].…”

Section: Introductionmentioning

confidence: 99%

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Sliding mode robust control of supersonic three degrees-of-freedom airfoils

Lee

Choo

et al. 2010

Int. J. Control Autom. Syst.

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The robust aeroelastic control of a three-degrees-of-freedom (3DOF) linear and non-linear wing-flap system under sliding mode control (SMC) and operation in supersonic flight speeds is presented. Open-and closed-loop aeroelastic responses to blast and sonic-boom excitation in the wingflap system with uncertainty, as well as flutter analysis, are investigated along with the implementation of a Sliding Mode Observer (SMO). The effectiveness of control in reducing the amplitude of oscillation and preventing flutter instability is demonstrated. NOMENCLATURE a = Non-dimensional elastic axis position measured from the mid-chord, positive aft B = Ratio of the nonlinear to the linear pitching stiffness M, H, K= Mass, damping, and stiffness matrices b = Half-chord length e = Non-dimensional leading-edge flap position measured from the mid-chord, positive aft , a c F F = Aerodynamic and control load vectors , , h α β = Plunging, pitching, and flap displacements , I I α β = Mass moment of inertia per unit span of the wing-flap system about the elastic axis (EA) and of the flap about the flap axis (FA) of rotation, respectively , , h k k k α β = Stiffness parameters in plunging, torsional stiffness of the wing and flap about the EA , , ea L M H β = Total lift per span, aerodynamic moment, and hinge moment , , a ea l m h β = Non-dimensional aerodynamic lift, moment, and torque m = Airfoil mass per unit span M F , M f = Flutter speed and flight speed ρ ∞ = undisturbed density , U V ∞ = free stream speed and its nondimensional counterpart , r r α β = Non-dimensional radii of gyration of the wingflap system about EA , S x α α = Static unbalance about EA and its nondimensional counterpart , S x β β = Static unbalance about FA and its nondimensional counterpart , t τ = Time variable and its nondimensional counterpart κ = Polytropic gas coefficient

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Section: Resultsmentioning

confidence: 92%

Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

Sliding mode robust control of supersonic three degrees-of-freedom airfoils

Lee

Choo

et al. 2010

Int. J. Control Autom. Syst.

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“…Gupta first proposed LQG control in 1980 and compared it with conventional controllers [11]. Ahmad, S., A. and Na, S., et al have tried combining LQG with different feedback control strategies [12,13]. After 10 years of development, Franciszek combined the H ∞ method with LQG to give a theoretical solution for nonlinear aeroelastic vibrations [14], the H ∞ controller.…”

Section: Introductionmentioning

confidence: 99%

Comprehensive Engineering Frequency Domain Analysis and Vibration Suppression of Flexible Aircraft Based on Active Disturbance Rejection Controller

Liu

Tian

2022

Sensors

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The crash of an aircraft with an almost vertical attitude in Wuzhou, Guangxi, China, on March 21, 2022, has caused a robust discussion in the civil aviation community. We propose an active disturbance rejection controller (ADRC) for suppressing aeroelastic vibrations of a flexible aircraft at the simulation level. The ADRC has a relatively simple structure and it has been proved in several fields to provide better control than the classical proportional-integral-derivative (PID) control theory and is easier to translate from theory to practice compared with other modern control theories. In this paper, the vibration model of the flexible aircraft was built, based on the first elastic vibration mode of the aircraft. In addition, the principle of ADRC is explained in detail, a second-order ADRC was designed to control the vibration model, and the system’s closed-loop frequency domain characteristics, tracking effect and sensitivity were comprehensively analyzed. The estimation error of the extended state observer (ESO) and the anti-disturbance effect were analyzed, while the robustness of the closed-loop system was verified using the Monte Carlo method, which was used for the first time in this field. Simulation results showed that the ADRC suppressed aircraft elastic vibration better than PID controllers and that the closed-loop system was robust in the face of dynamic parameters.

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Robust aeroelastic instability suppression of an advanced wing with model uncertainty in subsonic compressible flow field

Song

Choo

et al. 2013

Aerospace Science and Technology

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Robust aeroelastic control of two-dimensional supersonic flapped wing systems

Cited by 11 publications

References 8 publications

Sliding mode robust control of supersonic three degrees-of-freedom airfoils

Sliding mode robust control of supersonic three degrees-of-freedom airfoils

Comprehensive Engineering Frequency Domain Analysis and Vibration Suppression of Flexible Aircraft Based on Active Disturbance Rejection Controller

Robust aeroelastic instability suppression of an advanced wing with model uncertainty in subsonic compressible flow field

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