ROTATIONAL DYNAMICS AND EQUILIBRIUM ORIENTATIONS OF A GRAVITATIONALLY STABILIZED SATELLITE AUGMENTED BY A CONSTANT SPEED ROTOR.
Rept. for Sep-Dec 68,
AEROSPACE CORP EL SEGUNDO CALIF ENGINEERING SCIENCE OPERATIONS
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The linearized differential equations of motion for a two-body gravitationally oriented satellite with a symmetric, constant speed rotor rigidly attached to the main body are derived. The conditions that must be satisfied by the satellite in circular orbit in order to maintain equilibrium are described, and the conditions that must be satisfied to ensure that an equilibrium orientation exists are shown to be isomorphic to the conditions for equilibrium of a gyrostat. A description of all possible equilibrium orientations, which is based upon the results of R. E. Roberson and R. Longman, is also included. The equations of motion are then presented for two specialized physical cases of interest. Both of the cases examined are four-degree-of-freedom systems with the hinge axis directed along a specified axis with respect to the main body and, at the same time, the symmetry axis of the constant speed rotor for each case is constrained to lie in a specified plane. Author
- Unmanned Spacecraft