<h2>AAS 95-415</h2><h2>Multiple Rigid Body Reorientation Using Relative Motion With Constrained Final System Configuration</h2><h4>D. S. Rubenstein and R. G. Melton, The Pennsylvania State University, University Park, PA</h4><h2> Abstract </h2>Using movable appendages on a spacecraft as a means of standard or redundant attitude control would be a valuable capability.  A controller designed to generate the maneuver commands that would cause the relative motions necessary to bring about the desired reorientations is tested with numerous cases representing a variety of dynamic conditions.   The controller is capable of accommodating many different system configurations and dynamic conditions, including the difficult case of non-zero system momentum.  Additionally, the controller can return the system configuration (the positions of the movable bodies relative to the main body) to its initial state at the conclusion of the reorientation.  Results of the test cases indicate that the controller is capable of nearly complete reorientations in all cases tested while meeting the system constraints.<br><br>