We treat the question of large rotational maneuver and vibration stabilization of NASA Spacecraft Control Laboratory Experiment System (SCOLE). The mathematical model of SCOLE System includes the dynamical equations for rigid body slew maneuver and three dimensional vibration of the rigid space shuttle, the flexible beam and the reflector with an offset mass. The contribution of this thesis lies in the development of two control systems based on (i) Euler angles or (ii) angular velocity components as output variables for large rotational maneuvers and vibration suppression of the SCOLE System. Nonlinear inversion theory is used for the design. The design approach taken here is to decompose the rigid mode control from vibration stabilization. (Abstract shortened with permission of author.)
