high-precision three-axis attitude control scheme is vitally important to deal with the overactuated spacecraft, as long as the overall performance through rapid response can be in general acquired. due to the fact that the rigid-flexible spacecraft is somehow applicable, in so many academic and real environments, there is a consensus among experts of this field that the new insights in develop...

In this paper, we study sensor fusion for the attitude stabilization of Micro Aerial Vehicles (MAVs), in particular mechanical flying insects. Following a geometric approach, a dynamic observer is proposed which estimates attitude based on kinematic data available from different and redundant bio-inspired sensors such as halteres, ocelli, gravitometers, magnetic compass and light polarization c...

With a focus on investigations in the area of overactuated spacecraft, a new high-performance robust three-axis finite-time attitude control approach, which is organized in connection with the quaternion based estimation scheme is proposed in the present research with respect to state-of-the-art. The approach proposed here is realized based upon double closed loops to deal with the angular rate...

Various methods are presented to control the attitude of satellite due to lack of information of yaw axis attitude so far.&#10In this paper, a new method is used which is more general and is applicable to all types of satellites, with at least one controller. &#10This method is not limited to YAW axis and can control the two other axes as well. One feature of this approach is the ability to be ...

in this paper, a finite-time control scheme is presented for stabilization ofthe satellite chaotic attitude around its equilibrium point whenits attitude is confused by a disturbed torque. controllers and settling timeof stabilizaton are obtained, based on the lyapunov stability theoremand finite-time control scheme. this method is satisfied for any initial condition.numerical simulations are ...

Various methods are presented to control the attitude of satellite due to lack of information of yaw axis attitude so far. In this paper, a new method is used which is more general and is applicable to all types of satellites, with at least one controller. This method is not limited to YAW axis and can control the two other axes as well. One feature of this approach is the ability to be modi...

This paper presents the development of a control system design to keep the spacecraft attitude at a prescribed sun vector. A bounded controller is proposed which utilizes the measured sun vector and spacecraft spin rates, and the control gains are model independent and can be tuned for individual axis. An adaptive control scheme is developed for control parameters to ensure closed-loop performa...

A control law for an Integrated Power/Attitude Control System (IPACS) for a satellite is presented in this paper. Four or more energy/momentum wheels in an arbitrary non-coplanar configuration and a set of three thrusters are used to implement the torque inputs. The energy/momentum wheels are used as attitude control actuators, as well as an energy storage mechanism, providing power to the spac...