  As part of the Bristol PROVE mission, a nano satellite in low Earth orbit
will be required to track a ground based target during a 400 second flyover.
This requires agile attitude control that will be achieved using a system of
flywheels. To calculate the necessary torque from these flywheels, a controller
was designed. Using newly derived equations of motion for the system, an
expression to optimise the gains was produced. With this controller,
simulations were run to evaluate the largest causes of error in target
pointing. Disturbance torques were safely handled by the controller, but led to
a 12% increase in wheel speeds, reaching 8325 rpm. This higher speed led to an
increased gyroscopic torque, reaching 10^-7 Nm in the worst case. However since
the flywheels can deliver 10^-5 Nm of torque, the controller could also correct
for this. Hardware performance was then varied to assess the effect of each
component on pointing accuracy. Attitude sensor noise was found to increase
pointing error by 1.9 degrees in the worst case. Minimum performance
requirements were then determined for each component in order to maintain an
acceptable pointing accuracy.
