A system for counteracting a disturbance in a spacecraft includes a biasing apparatus
that is coupled to the spacecraft and a spacecraft controller within the spacecraft.
The disturbance has a known sign, magnitude and time. The biasing apparatus controls
the biasing apparatus to place the spacecraft in a first dynamic state or position
as a function of the sign, magnitude, and time of the disturbance. The controller
also controls the spacecraft to a second dynamic state as a function of the known
sign, magnitude, and time so that the spacecraft is oriented in a position other
than the desired orientation so that after the disturbance the spacecraft is oriented
in the desired orientation in response to the disturbance. The biasing apparatus
may comprise a momentum wheel and the disturbance may comprise thrusting firing
used for controlling momentum dumping.
