A Movable-Mass Attitude Stabilization System For Cable-Connected Artificial-^ Space Stations
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The development of an active, momentum-exchange system to be used for attitude stabilization of a class of cable-connected artificial-g space stations is studied. A system which employs a single movable control mass is examined for the control of a space station which has the physical appearance of two cylinders connected axially by cables. The dynamic model for the space station includes its aggregate rigid body rotation and relative "torsional" rotation between the bodies. A zero torsional stiffness design (one cable) and a maximum torsional stiffness design (eight cables) are examined in various (0, 1/4, 1/2, 3/4, 1) stages of deployment, for selected spin velocities ranging from 4 rpm upwards. A linear, time-invariant, feed-back control system is employed, with gains calculated via a root-specification procedure. The movable mass controller (MMC) provides critical wobbledamping capability for the crew quarters for all configurations and spin velocity. The complete MMC system has a projected Earth weight of approximately 500 Ibs. For the fully-deployed space station examined in this study, at the nominal spin-velocity of 4 rpm, the peak-force requirements for the system are on the order of 15 Ib for the maximum stiffness design, and 5 Ib for the zero stiffness design. The corresponding mechanical power requirements for the system are 6 and 36 w for the zero and maximum stiffness designs, respectively. American Institute of Aeronautics and Astronautics, Inc., 1974, All rights reserved.
