The invention discloses an
attitude control system for
space vehicle and a method thereof. The
control system has only one biased
momentum wheel, one set of tri-axial magnetic torquer and one attitude controller loaded with
algorithm. The method comprises a step of rate damping controlling, a step of initially capturing controlling and a step of stationarity controlling. At the rate damping stage, geomagnetism change is used to control the magnetic control of three passages of a
satellite by B-dot; at the initially capturing stage, the magnetic control is realized, PD control is performed by pitching and the passages are rolled and yawed to carry out
nutation and
precession composite control; at the stationarity controlling stage, the magnetic control is realized, PD control is performed by pitching and the passages are rolled and yawed to carry out
nutation and
precession composite control. The capturing stage and the stationarity controlling stage fully depend on magnetic torquer to perform positive magnetic control, thereby changing which a
satellite only uses a magnetic torquer to carry out unload of the
momentum wheel or auxiliary magnetic control, so as to refine
system configuration to further improve reliability of the
system.
Momentum of a
satellite is biased to rotate on the ground, so as to ensure stable separation of the satellite without performing air injection control. Therefore, the magnetic torquer can be used for realizing fast and stable
initial rate damping.