  The attitude stabilization of a micro-satellite employing a
variable-amplitude cold gas thruster which reflects as a time varying gain on
the control input is considered. Existing literature uses a persistence filter
based approach that typically leads to large control gains and torque inputs
during specific time intervals corresponding to the 'on' phase of the external
actuation. This work aims at reducing the transient spikes placed upon the
torque commands by the judicious introduction of an additional time varying
scaling signal as part of the control law. The time update mechanism for the
new scaling factor and overall closed-loop stability are established through a
Lyapunov-like analysis. Numerical simulations highlight the various features of
this new control algorithm for spacecraft attitude stabilization subject to
torque intermittence.
