Accession Number : AD0699566
Title : ROTATIONAL DYNAMICS AND EQUILIBRIUM ORIENTATIONS OF A GRAVITATIONALLY STABILIZED SATELLITE AUGMENTED BY A CONSTANT SPEED ROTOR.
Descriptive Note : Rept. for Sep-Dec 68,
Corporate Author : AEROSPACE CORP EL SEGUNDO CALIF ENGINEERING SCIENCE OPERATIONS
Personal Author(s) : Williamson,Robert K.
Report Date : 15 JUL 1969
Pagination or Media Count : 54
Abstract : 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)
Descriptors : (*SATELLITES(ARTIFICIAL), STABILIZATION SYSTEMS), (*ATTITUDE CONTROL SYSTEMS, SATELLITES(ARTIFICIAL)), GRAVITY, CIRCULAR ORBITS, EQUATIONS OF MOTION
Subject Categories : Unmanned Spacecraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE