Non colocated rate sensing for control moment gyroscopes
US5875676A · kind A · utility
12Cited by
3References
14Claims
0Family size
Assignee
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Key dates
| Filing date | Sep 2, 1997 |
| Grant date | Mar 2, 1999 |
| Priority date | — |
| Expiry date | Sep 2, 2017 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T74/1229
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A feedback system for use in controlling control moment gyroscopes that are used in positioning a spacecraft where the relative rate of rotation is determined from the difference between the rotation rate of the gimbals of the CMGs and the rotation rate of the frame about the gimbal axis. The inertial reference units on the spacecraft are utilized as the source of measured rates of rotation of the three spacecraft axes with respect to a predetermined axis and these are converted to the rates of rotation of the frame about the individual CMG gimbal axes.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.