TY - JOUR

T1 - Stabilization of a programmed rotation mode for a satellite with electrodynamic attitude control system

AU - Aleksandrov, A. Yu

AU - Aleksandrova, E. B.

AU - Tikhonov, A. A.

PY - 2018/4/17

Y1 - 2018/4/17

N2 - The paper deals with a dynamically symmetric satellite in a circular near-Earth orbit. The satellite is equipped with an electrodynamic attitude control system based on Lorentz and magnetic torque properties. The programmed satellite attitude motion is such that the satellite slowly rotates around the axis of its dynamical symmetry. Unlike previous publications, we consider more complex and practically more important case where the axis is fixed in the orbital frame in an inclined position with respect to the local vertical axis. The satellite stabilization in the programmed attitude motion is studied. The gravitational disturbing torque acting on the satellite attitude dynamics is taken into account since it is the largest disturbing torque. The novelty of the proposed approach is based on the usage of electrodynamic attitude control system. With the aid of original construction of a Lyapunov function, new conditions under which electrodynamic control solves the problem are obtained. Sufficient conditions for asymptotic stability of the programmed motion are found in terms of inequalities for the values of control parameters. The results of a numerical simulation are presented to demonstrate the effectiveness of the proposed approach.

AB - The paper deals with a dynamically symmetric satellite in a circular near-Earth orbit. The satellite is equipped with an electrodynamic attitude control system based on Lorentz and magnetic torque properties. The programmed satellite attitude motion is such that the satellite slowly rotates around the axis of its dynamical symmetry. Unlike previous publications, we consider more complex and practically more important case where the axis is fixed in the orbital frame in an inclined position with respect to the local vertical axis. The satellite stabilization in the programmed attitude motion is studied. The gravitational disturbing torque acting on the satellite attitude dynamics is taken into account since it is the largest disturbing torque. The novelty of the proposed approach is based on the usage of electrodynamic attitude control system. With the aid of original construction of a Lyapunov function, new conditions under which electrodynamic control solves the problem are obtained. Sufficient conditions for asymptotic stability of the programmed motion are found in terms of inequalities for the values of control parameters. The results of a numerical simulation are presented to demonstrate the effectiveness of the proposed approach.

KW - Asymptotic stability

KW - Attitude motion

KW - Biaxial rotation

KW - Satellite

KW - Stabilization

KW - UNDERACTUATED SPACECRAFT

KW - SPIN-AXIS STABILIZATION

KW - CONFIGURATION

KW - RIGID SPACECRAFT

KW - TORQUES

KW - GEOMAGNETIC-FIELD

KW - RADIATION

UR - http://www.scopus.com/inward/record.url?scp=85046123908&partnerID=8YFLogxK

UR - http://www.mendeley.com/research/stabilization-programmed-rotation-mode-satellite-electrodynamic-attitude-control-system

U2 - 10.1016/j.asr.2018.04.006

DO - 10.1016/j.asr.2018.04.006

M3 - Article

AN - SCOPUS:85046123908

VL - 62

SP - 142

EP - 151

JO - Advances in Space Research

JF - Advances in Space Research

SN - 0273-1177

IS - 1

ER -