Method and apparatus for using a momentum bias to provide spacecraft attitude stabilization during an eclipse
US6260806A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jun 3, 1999 |
| Grant date | Jul 17, 2001 |
| Priority date | — |
| Expiry date | Jun 3, 2019 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/281
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The attitude of a spacecraft is controlled during an eclipse without the dependence on auxiliary power by configuring the spacecraft so that it will receive solar power after solar eclipse is passed. The spacecraft is then oriented with respect to a sun line. The spacecraft is then spun so that it maintains a desired angular momentum throughout the eclipse and provides passive stabilization of the attitude. After the eclipse has passed, the spacecraft power is restored and the spacecraft attitude is detected. All spacecraft units are then powered up and thereafter, normal on-station attitude is re-established and normal spacecraft operations are established.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.