Linear covariance techniques for attitude dynamics
determination on a small satellite

Abstract: A spin-stabilized spacecraft is designed to rotate around one of its
principal axes. However, geometric factors such as products of inertia, and
environmental factors such as external disturbance torques can cause the
spacecraft to precess. In this thesis, Linear Covariance Analysis is
implemented to quantify how the coelevation angle of a spacecraft relates to
normally distributed variations in a set of a geometric and enviromental
input parameters. Further, a Matlab software tool for implementing
Linear Covariance Analysis on Simulink computer models is presented.