Isolation flexure for gyroscopes
AssigneeSperry Corporation
InventorsVirgil O. Bennett, George W. Wilson
Life of this patent
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Abstract
An illustrative embodiment of the invention provides an isolation flexure assembly for the control moment gyroscope of a spacecraft attitude control system for attenuation of vibratory disturbances therein, due to rotor static and dynamic unbalance and spin bearing radial forces. The isolation flexure assembly isolates the rotor, the main generator of the vibratory disturbances, from the spacecraft permitting ultraprecise pointing or precision torquing of the spacecraft.
Claims4
A gyroscopic device including a rotor assembly adapted to spin about an axis, a gimbal assembly for rotatably mounting the rotor about an axis perpendicular to the spin axis and oppositely disposed and aligned module assemblies including bearing means for receiving the gimbal assembly for rotation wherein said device comprises:
- isolation flexure means disposed between and coupled to the gimbal assembly and respective modules, said isolation flexure means being aligned in a plane perpendicular to the gimbal and rotor output axes and parallel to the spin axis,
- said isolation flexure means having a predetermined relative low stiffness in the plane of the gimbal and output axes and a predetermined relative high stiffness along the spin axis and about the gimbal and output axes, and
- whereby said isolation flexure means attenuates vibratory disturbances emitted by the rotor assembly to the module assemblies along the gimbal and output axes and insures torsional stiffness about the output axis.
A gyroscopic device according to claim 4 wherein said bar includes a pilot portion axial to and juxtaposed to one of said threaded end portions for accurate assembly into the rotor assembly and to accommodate relative sliding motion.
Dependencies are inferred from the claim text.