Invariant manifold techniques for attitude control of symmetric spacecraft

In this paper we consider the problem of attitude stabilization of an axially symmetric spacecraft using two pairs of gas jet actuators to generate control torques about two axes spanning the two-dimensional plane orthogonal to the axis of symmetry. Under the assumption that the initial spin rate about the symmetry axis is zero, and using a new kinematic formulation, we construct an invariant manifold for the closed loop system with a specific feedback law. Using this manifold we derive a stabilizing control law which achieves arbitrary reorientation of the spacecraft