Control of the attitude of a satellite in low orbit involving solar acquisition
US5788188A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Dec 5, 1996 |
| Grant date | Aug 4, 1998 |
| Priority date | — |
| Expiry date | Dec 5, 2016 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/366
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
For controlling the attitude of the body of an earth satellite placed on a low orbit, values of components of the geomagnetic field of the earth are measured along three axes of a frame of reference bound to the body. The values are derivated with respect to time, and multiplied by a gain. Currents responsive to the multiplicated derivatives are passed through magnetic torquers located along the three axes of the body to create magnetic torques that bias the body to a fixed angular position relative to the field lines of the geomagnetic field. Such steps are continuously carried out during eclipse periods. Out of eclipse periods, the pitch of the body is controlled by modifying an internal momentum in response to a signal provided by a solar sensor, so as to maintain solar generators carried by the body of the satellite oriented towards the Sun.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.