Continuous robust control for aeroelastic vibration control of a 2-D airfoil under unsteady flow

Abstract

In this paper, a particular class of 2-D aeroelastic systems accounting for structural nonlinearities in pitching displacement and operating in an unsteady aerodynamic incompressible flowfield description is considered. By using the flap hinge torque of a trailing-edge flap surface as the control input, a continuous controller is proposed to suppress the aeroelastic vibrations of the wing section model. The control design based on the choice of the pitching angle as the output variable yields a semi-global asymptotic stability result. Furthermore, the system is theoretically shown to be robust to external disturbances. Numerical simulation results verify the efficacy of the proposed control strategy toward suppressing aeroelastic vibration in both pre-and post-flutter flight speed regimes under a multitude of external disturbances.

Sliding mode-based continuous guidance law with terminal angle constraint

“…in finite time. Furthermore, combing Equations (34) and 36, we have LOS angle error converges into the region…”

“…For the former one, most of them are derived by using linear-quadratic optimal control theory or biased-PNG concept based on linearised engagement geometry for non-manoeuvring targets, such as sub-optimal guidance law (15) , optimal guidance law (16,17) , time-to-go weighted polynomial guidance law (18)(19)(20) , generalised impact angle guidance law (21) , and biased PNG law (22)(23)(24)(25)(26)(27)(28) . For the non-linear case, SMC is quite frequently used to obtain impact angle guidance laws, such results can be found in Refs 29-33, due to its inherent robustness against external disturbances (34)(35)(36) . However, all SMCbased guidance laws mentioned above used a discontinuous sign function to guarantee the robustness against target manoeuvre except for Ref.…”

Improved Grey Particle Swarm Optimization and New Luus‐Jaakola Hybrid Algorithm Optimized IMC‐PID Controller for Diverse Wing Vibration Systems

“…In the wing vibration control system, the proportionalintegral-derivative (PID) controller [6,8] has been developed and most widely used to suppress the vibrations for linear wing vibration system. For nonlinear wing vibration systems, sliding mode control [9,10], robust control [11,12] and H ∞ control [13] have been studied to control aeroelastic vibrations under unsteady ow and nonlinear spring. To deal with multipleinput-multiple-output (MIMO) wing vibration system, a state estimation based adaptive output feedback controller [14] was designed for vibration suppression on a nonlinear wing section.…”

Nonlinear optimal control for active suppression of airfoil flutter via a novel neural-network-based controller

“…These advanced methods include but are not limited to: online updated linear quadratic regulator [4], [5], linear-parameter-varying techniques [6], [7], feedback linearization [8], [9], model reference adaptive control [10], back-stepping-based adaptive output feedback control [11], *This work was supported by the Sir Ross and Sir Keith Smith Fund. The authors are with the School of Mechanical Engineering, The University of Adelaide, Adelaide, SA 5005, Australia lei.chen@adelaide.edu.au [12], robust output feedback control [13], modular adaptive control [14], [15], modified filtered-X least-mean-square control [16], L 1 adaptive control [17], sliding-mode control [18], finite-time H ∞ adaptive fault-tolerant control [19], [20] and neural network based adaptive control [21]- [23], etc.…”