Boundedness of Spacecraft Hovering Under Dead-Band Control in Time-Invariant Systems (original) (raw)

Spacecraft's Partially Invariant Stabilization System Spacecraft's Partially Invariant Stabilization System

IOP Conference Series: Materials Science and Engineering, 2020

In most of the known spacecraft stabilization systems the control signal in the centre of mass movement channel is generated according to proportional plus integral control law, based on the measurements of tangential velocity of the centre of mass and its integral-linear drift. In the angular stabilization channel, the control signal shall be generated in proportion to the spacecraft deviation angle in the transverse plane and the angular velocity of the spacecraft rotation in this plane. In practice, a spacecraft's stabilization system, which is partially invariant to the disturbing moment, is the easiest to implement. The velocity performance limitation of the control actuator has the most influence upon stability of the system among all the nonlinearities considered in the mathematical modelling. Therefore, we shall consider a model of an invariant stabilization system with due regard to nonlinearity. For the system under consideration, it is possible to construct lines of equal values of the auto oscillation amplitude in a two-parameter plane. The study of the stability of the proposed partially invariant stabilization system revealed that it is possible to ensure sufficient stability margins in the system under consideration by choosing parameters for the stabilization controller. At the same time, it allows to provide high quality of the transition process.

Mathematical review of the attitude control mechanism for a spacecraft

INCAS BULLETIN, 2020

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 o...

Multirate three axes attitude stabilization of spacecraft

Proceedings of the 28th IEEE Conference on Decision and Control, 1989

... S. Monaco*, D.Normand-Cyrot** and S. Stomelli*** ... In section three, two sets of equations for modelling the space craft dynamics are setted; an ideal one for simulation purpose and a simplified one for elaborating the control scheme; digital control laws are computed. ...