No abstract

No abstract

No abstract

Summary In this article, an integrated multiinput multioutput model reference adaptive control algorithm is presented based on active front steering and effective direct yaw moment distribution as an advanced driver assistance system. Vehicle parameter uncertainties in mass and tire‐road friction coefficient are considered through adaptation laws at the upper level in the control structure. The efficient distribution of yaw moment on the rear wheels is performed via a constrained optimization at the lower control level. Control commands are executed by additive steering angle on front wheels and brake torque applied on one of the rear wheels. Simulation results for different lateral maneuvers are employed for the evaluation of the proposed adaptive control method. The performance of the integrated control algorithm to enhance vehicle handling and stability is shown on various road conditions.

Purpose – The purpose of this paper is to design a stable controller such that the control input is applied to the delta-wing aircraft in order to adjust the roll dynamics. The controller must provide a desired tracking performance with minimum tracking error. Design/methodology/approach – In this paper, the second level adaptation (SLA) strategy is applied to control a delta-wing aircraft using multiple models. The implemented control structure is compared with the first level adaptation (FLA) and model reference adaptive control (MRAC) techniques. Findings – SLA architecture not only copes with a wide uncertainty domain caused by aerodynamic effects, but also its rapid and accurate convergence is one of its most important features. Furthermore, this strategy makes a smoother control signal with respect to FLA and MRAC even at the same initial times. It should be also noted that SLA using three models, copes with uncertainty that may occur to the aircraft at high Angle Of Attacks (AOAs) at the entire flight envelope. Originality/value – In this paper for the first time the application of this strategy is used to identify and control a delta-wing aircraft. Furthermore a systematic block diagram approach is proposed for the design.