Mathematical review of the attitude control mechanism for a spacecraft

Abstract

The issue of inertial pointing for a spacecraft with magnetic actuators is considered and a practical global response to this problem is obtained by static attitude and speed feedback methods. A local solution dependent on dynamic attitude feedback is additionally introduced. The simulation results show the practical applicability of the proposed approach. The issue of attitude regulation of rigid spacecraft, i.e., spacecraft demonstrated by the Euler's conditions and by an appropriate parameterization of the attitude, has been broadly concentrated as of late. As a matter of first importance, it is beyond the realm of imagination by methods for magnetic actuators to give three autonomous control torques at each time instant. Moreover, the conduct of these actuators is characteristically time-varying, as the control instrument relies on the varieties of the Earth magnetic field along the spacecraft orbit. In any case, demeanor adjustment is conceivable in light of the fact that on normal the framework has solid controllability properties for a wide range of orbit inclinations. A lot of work has been devoted as of late to the issues of examination and structure of attractive control laws in the straight case, i.e., nominal operation of a satellite near its equilibrium attitude. Specifically, ostensible and vigorous solidness and execution have been contemplated, utilizing either devices from occasional control hypothesis misusing the (quasi) intermittent conduct of the framework close to an equilibrium or other techniques aiming at developing suitable time-varying controllers.

Keywords

• euler angle
• quaternion
• kalman filtering (ekf
• ukf)