This paper presents the problem of designing the functional behaviour of the interaction between two side stick con trollers an autopilot and a ight control computer in a y by wire aircraft Two models are developed using the ISO formal description technique LOTOS and analysed us ing rigorous abstract testing techniques

This paper presents a simple unknown input estimation technique using generalized matrix inverse. The full order observer constructed by g-inverse is extended and implemented for this purpose. The necessary and sufficient condition has been introduced for existence of such an estimator. The proposed method is illustrated by numerical example (Two loop autopilot in pitch plane) and the MATLAB si...

This paper considers application of L1 adaptive output feedback controller to a missile longitudinal autopilot design. The proposed adaptive controller has satisfactory performance in the presence of parametric uncertainties and time-varying disturbances. Simulations demonstrate the benefits of the control method and compare the results to Linear Quadratic Regulator (LQR) and Linear Quadratic G...

The recent introduction of smart glasses through media spurred new concepts of service support systems. Especially in the domain of Technical Customer Services (TCS), the opportunity to access information hands-free provides additional benefits. However, due to the novelty of the technology besides various technical issues the question of usefulness is of vital importance. To date, little resea...

Sliding mode control of a launch vehicle during its atmospheric flight phase is studied in the presence of unmatched disturbances. Linear time-varying dynamics of the aerospace vehicle is converted into a systematic formula and then dynamic sliding manifold as an advanced method is used in order to overcome the limited capability of conventional sliding manifolds in minimizing the undesired eff...

The mixed sensitivity design method for multivariable linear control systems proposed in the companion paper (Kwakernaak, 2001) is applied to the design of a stability augmentation system for the longitudinal motion of a fighter airplane previously studied by Safonov and Chiang (1988). Both H∞ and 2 H mixed sensitivity design are considered. They lead to quite similar results. Copyright © 2002 ...

“Naše more” 62(4)/2015., pp. 243-246