Method and apparatus for contingency guidance of a CMG-actuated spacecraft
US9038958B1 · kind B1 · utility
7Cited by
8References
20Claims
0Family size
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Key dates
| Filing date | May 23, 2013 |
| Grant date | May 26, 2015 |
| Priority date | — |
| Expiry date | Sep 17, 2033 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/245
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
Methods and apparatus are presented for spacecraft operation using non-Eigen axis attitude transitions via control momentum gyroscopes (CMGs) to avoid or mitigate singularities by providing a time-varying attitude command vector including a plurality of time-varying attitude command signals or values representing a plurality of spacecraft states and control trajectories as a guidance command input to an attitude controller of the spacecraft without modifying the spacecraft feedback control law.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.