Title: ATTITUDE CONTROL OF A FLEXIBLE, SPINNING, TOROIDAL MANNED SPACE STATION
Abstract: In this paper, a system is considered for controlling the direction of the spin axis of a nonrigid, toroidal manned space station. After selection of a control system suitable for a rigid vehicle, the basic objective is to find locations within the space station for control actuators (forces or moments) and attitude sensors to ensure stability of the space station and to minimize the excitation of vibration by the control system. For a linear control system, expanding the system's characteristic equation about the normalized flexural modal poles yields general relationships that must be satisfied in locating sensors and actuators to stabilize flexible motions. Applying these relations to the spinning space station makes it possible to observe the influence of actuators and sensors on station stability so that suitable locations can be selected for them.