2016
DOI: 10.1007/s13369-016-2113-7
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Improving Performance for Nonlinear Aeroelastic Systems via Sliding Mode Controller

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Cited by 7 publications
(4 citation statements)
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“…where H ∈ R N ×1 is defined as in (18), and S ∈ R N ×N is a symmetrical positive-definite matrix with initial state S(0) = S(0) T 0. Note that the matrix P proposed and discussed in [24] is constant and hence does not suit a wide flight envelop with varying airspeed U ∞ .…”
Section: B Nn-based Value Function Approximation (Vfa)mentioning
confidence: 99%
See 1 more Smart Citation
“…where H ∈ R N ×1 is defined as in (18), and S ∈ R N ×N is a symmetrical positive-definite matrix with initial state S(0) = S(0) T 0. Note that the matrix P proposed and discussed in [24] is constant and hence does not suit a wide flight envelop with varying airspeed U ∞ .…”
Section: B Nn-based Value Function Approximation (Vfa)mentioning
confidence: 99%
“…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.…”
Section: Introductionmentioning
confidence: 99%
“…To overcome chattering and ensure a finite-time fast system stabilization, SMC is combined with many other controllers [21][22][23][24][25][26]. Second order SMC was combined with the backstepping technique in [22] by adding a disturbance and uncertainty compensator term in the controller's expression, and a modified high order SMC containing a time continuous function describing nonlinearities was proposed in [23]. Both studies were effective in removing LCOs and stabilizing the system in a finite time.…”
Section: Introductionmentioning
confidence: 99%
“…The main contributions of this work are:  To introduce unsteady aerodynamics in the nonlinear aeroelastic system model using the Wagner's function. Thing that has not been investigated in the previous works in AFS field like in [22] and [23].…”
Section: Introductionmentioning
confidence: 99%