A switching neural network control scheme, consisting of the adaptive controller and sliding mode controller, is proposed for underactuated formation reconfiguration in elliptic orbits with loss either radial or in-track thrust. By using inherent coupling system states, technique then adopted to estimate unmatched disturbances design achieve high precision. The works active region, composed lin...

The Gamma modeling technique is a finite SRGM-based modeling technique. Prior work uses this technique to fit a SRGM based on the Gamma function using software process metrics that measure development defects and then uses the fitted model to make predictions. The cost of use of this technique is lower than typical. Overview Inputs • The occurrence time of each development defect or the defect ...

Robust control for nonlinear uncertain systems has been solved for matched uncertainty but has not been completely solved yet for unmatched uncertainty. This paper developed a new method in which an adaptive radial basis function neural network is used to compensate for the effects of unmatched uncertainty in the framework of integral sliding mode control. The stability of the whole system is g...

This paper deals with the output tracking problem of a MIMO system subjected to a class of actuator faults and unmatched perturbations. The proposed methodology is based on high order sliding mode observation and identification techniques. A dynamic sliding surface is proposed using a backstepping-like design strategy in order to counteract the effects of the unmatched perturbations. Whereas a ...

Abstract: This paper deals with asymptotic rejection of unmatched general periodic disturbances in nonminimum phase nonlinear output feedback systems. The steady state responses are defined for unstable systems subject to general periodic disturbances, and the generalized gain and phase are defined for stable systems subject to general periodic disturbances. Based on the new definitions, new re...

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...