Escaping singularities in a satellite attitude control
US6047927A · kind A · utility
25Cited by
5References
1Claims
0Family size
Assignee
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Key dates
| Filing date | Mar 16, 1998 |
| Grant date | Apr 11, 2000 |
| Priority date | — |
| Expiry date | Mar 16, 2018 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/36
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
Control moment gyros in an array are rotated to reorient a satellite by an attitude signal. If the signal causes a gyro to have position that will produce a singularity in attitude control, a disturbance is introduced into the signal to avoid the singularity.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.