This paper describes an approach for controlling the attitude of statically unsable thrust-levitated vehicles in hover or slow translation. The large thrust vector that characterizes such vehicles can be modulated to provide control forces and moments to the airframe, but such modulation is accompanied by significant unsteady flow effects. These effects are difficult to model, and can compromis...

In the speed sensorless vector control system, the amended method of estimating the rotor speed about model reference adaptive system (MRAS) based on radial basis function neural network (RBFN) for PMSM sensorless vector control system was presented. Based on the PI regulator, the radial basis function neural network which is more prominent learning efficiency and performance is combined with M...

In this paper, a sliding mode control is presented for direct torque and stator flux of interior permanent magnet synchronous motor in rotor speed sensorless drive system. The scheme developed specific rotating reference frame (X-Y) which the current space vector coincides with (X) axis. For technique no need to have any knowledge machine parameters such as two-axis inductances, magnets linkage...

Sensor network attitude problem consists in retrieving the attitude of each sensor of a network knowing some relative orientations between pairs of sensors. The attitude of a sensor is its orientation in an absolute axis system. We present in this paper a method for solving the sensor network attitude problem using quaternion formalism which allows to apply linear algebra tools. The proposed al...

In this paper, an adaptive backstepping technique based fault tolerant control scheme is developed for a spacecraft attitude stabilization system, in which the external disturbances and partial loss of actuator effectiveness fault are considered. More specifically, using the adaptive backstepping control method, a baseline control law is first proposed for the normal system without actuator fau...

This paper considers the coupled orbit and attitude dynamics of a dumbbell spacecraft around an asteroid. Geometric methods are used to derive the coupled equations of motion, defined on the configuration space of the special Euclidean group, and then a nonlinear controller is designed to enable trajectory tracking of desired landing trajectories. Rather than relying on sliding mode control or ...

Reaction wheels are key components for the spacecraft attitude control subsystems. Faults in reaction may lead to high energy consumption, lack of control, and case failure, loss spacecraft. The accurate identification anomalies is a challenging task due internal nonlinearities wheels. This study proposes fast end-to-end architecture detecting identifying occurring using One-Dimensional Convolu...

This paper presents adaptive add-on control algorithms for the conventional mode of operation of MEMS z-axis gyroscopes. This scheme is realized by adding an outer loop to a conventional force-balancing scheme that includes a parameter estimation algorithm. The parameter adaptation algorithm estimates the angular rate, identifies and compensates the quadrature error, and may permit on-line auto...