Direct Model Reference Adaptive Internal Model Controller using Perrin equation Adjustment Mechanism for DFIG Wind Farms

Adjustment mechanism with sliding mode for adaptive PD controller applied to unmanned fixed-wing MAV altitude

“…Where θ m is the output from the reference model, we have followed the methodology that has been presented in [9] for the MIT rule, taking this into account, the aerodynamic model has been transformed into the representation of a transference function to develop the derivatives of sensitivity; these have been obtained by computing partial derivatives concerning the controller parameters kpa and kva . Thus, the closed-loop transfer function with the adaptive PD controller has been defined as (10).…”

“…Still, the difference is that in [8] the PID is used between other controllers based in MRAC and the plant, the proposed of [8] has the objective of improving the transient response of the plant, and it uses the known MRAC structure [9]. Whereas in [10] the direct model reference adaptive and an internal controller is applied to doubly fed induction generator and in this work, is proposed the adjustment mechanism based on MIT rule. Still, in addition, the Perrin equation has been added to this mechanism with an improved internal model controller filter design.…”

“…Still, in addition, the Perrin equation has been added to this mechanism with an improved internal model controller filter design. Thus, in [10] the adjustment mechanism using the Perrin equation is intending to avoid the selection of the adaptive gain by a heuristic method.…”

“…Riache et al [12] is presented an adaptive robust controller applied to quadrotor with a serial robot manipulator onboard, the control objective in [12] is that during the flight, move the robot arm and keep the desired trajectory. On the other hand, the works [7], [8], [10], [11] presents simulations results using the Matlab software as well as in this work. We can find other adaptive controllers applied to fixed-wing unmanned aerial vehicle (UAV) as in [13] where is presented the guidance system makes the airplane follows pre-computed references using a novel iterative model predictive scheme, which can handle the nonlinear optimization problem by successive linearizations (starting the algorithm using a robust l 1 navigation law.…”

On Intrinsic Geometric Stability of Controller

“…[5]. Similar direct model reference adaptive controllers [6,7,8] are explored in diverse applications.…”