In this study, attitude control is proposed for helicopters with actuator dynamics. For the nominal helicopter dynamics, model-based control is firstly presented to keep the desired helicopter attitude. To handle the model uncertainty and the external disturbance, radial basis function neural networks are adopted in the attitude control design. Using neural network approximation and the backste...

The Ørsted satellite mission imposes comparatively high requirements on autonomy of the attitude control system. Cost requirements, on the other hand, impose simple hardware and cheap actuators in form of magnetorquer coils. These conflicting requirements are fulfilled through development of novel attitude and control algorithms and wide on-board autonomy. The entire control and attitude determ...

Conventional quaternion based methods have been extensively employed for spacecraft attitude control where the aerodynamic forces can be neglected. In the presence of aerodynamic forces, the flight attitude control is more complicated due to aerodynamic moments and inertia uncertainties. In this paper, a robust nero-adaptive quat...

This paper proposed a nonlinear robust control for spacecraft attitude based on passivity and disturbance suppression vector. The spacecraft model was described using quaternion. The control law introduced the suppression vector of external disturbances and had no information related to the system parameters. The desired performance of spacecraft attitude control could be achieved using the des...

A continuous feedback controller with a periodic time varying term for the attitude control of an un-deractuated rigid spacecraft is derived. The attitude is described with the Euler parameter vector. Due to the nondiierentiable nature of exponential stabilizers , sampling of some measurements is used. Global exponential convergence is indicated with analysis and simulations.

The stability of spacecraft attitude is studied with considering sinusoidal disturbance. A passive attitude controller without angular velocity measurement for spacecraft described by quaternion is designed. The passive controller has no information related to system parameters. So it has robustness to model error and uncertainty of model parameters. The stability of spacecraft attitude control...

An output feedback control law is proposed in this paper for spacecraft attitude reorientation task. Although maneuver has been widely investigated and obtained significant results, it still challenging when considering pointing constraints lacking the information of angular velocity. Firstly, potential function introduced to tackle constraints. Then, by jointly designing sign function, anti-un...