Attitude control law design for spacecraft large angle maneuvers is investigated in this paper. The feedback linearization technique is applied to the design of a nonlinear tracking control law. The output function to be tracked is the quaternion attitude parameter. The designed control law turns out to be a combination of attitude and attitude rate tracking command. The attitude-only output fu...

Based on the characteristics of the attitude control system, this paper use the neural network predictive model controller which can identify accurately attitude system and obtain real-time control sequence applied to the controlled object through the model prediction, feedback correction and rolling optimization each link to complete motion attitude control of unmanned aerial vehicle. This con...

This paper presents the use of the predictive fuzzy logic controller (PFLC) applied to attitude control system for agile micro-satellite. In order to reduce the effect of unpredictable time delays and large uncertainties, the algorithm employs predictive control to predict the attitude of the satellite. Comparison of the PFLC and conventional fuzzy logic controller (FLC) is presented to evaluat...

Neural networks offer a unique approach to controlling a dynamically changing system. By updating synaptic weights of an interconnected, algebraic framework, desired system objectives can be reached despite an unknown operating environment. This research implements a neural network for controlling the attitude of a satellite with unknown system disturbances. The training and updating of the con...

Recent quadrotors have transcended conventional designs, emphasizing more on foldable and reconfigurable bodies. The state of the art still focuses mechanical feasibility such designs with limited discussions tracking performance vehicle during configuration switching. In this letter, we first present a common framework to analyse attitude errors folding quadrotor via theory switched systems. W...

The robust optimal attitude control problem for a flexible spacecraft is considered. Two optimal sliding mode control laws that ensure the exponential convergence of the attitude control system are developed. Integral sliding mode control ISMC is applied to combine the first-order sliding modewith optimal control and is used to control quaternion-based spacecraft attitudemanoeuvres with externa...

One of the simplest and most popular methods to design a model-based controller for nonlinear dynamic system is apply linear control theories linearized model system. For linearization, first-order Taylor series expansion straightforward widely used method. Although related linearization method fairly simple, unfortunately, it causes an error in model, especially highly systems. Different strat...