Equatorial-normal body-stabilized spacecraft and control method for inclined orbit operation
US6318676A · kind A · utility
8Cited by
3References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jan 10, 2000 |
| Grant date | Nov 20, 2001 |
| Priority date | — |
| Expiry date | Jan 10, 2020 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/66
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A control method and improved equatorial-normal body-stabilized spacecraft that operates in an inclined orbit. The control method controls pointing of payloads (communication antennas and instruments) and solar arrays disposed on the spacecraft. The method controls the spacecraft to provide Earth-pointing payloads and sun-pointing solar arrays so that the spacecraft body and solar arrays each rotate only around a single axis, a pitch axis of the spacecraft.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.