Spacecraft control with skewed control moment gyros
US5681012A · kind A · utility
15Cited by
4References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 5, 1995 |
| Grant date | Oct 28, 1997 |
| Priority date | — |
| Expiry date | Jan 5, 2015 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/36
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A method of and system for applying single gimbal control moment gyros to spacecraft attitude control employing two control moment gyros with nominal spin axes anti-parallel and gimbal axes displaced at a fixed angle in the plane normal to the nominal spin axes to achieve two orthogonal body fixed control torques using two wheels. If the gimbal axis displacement of each of three wheels is 120 degrees, two wheels provide independent uncoupled orthogonal two-axis control, and the third can substitute, in the event of failure, for either of the two requiring no change in control law or performance.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.