Method of controlling the attitude control for satellites on an orbit inclined relative to the equator
US5794891A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Jan 3, 1996 |
| Grant date | Aug 18, 1998 |
| Priority date | — |
| Expiry date | Jan 3, 2016 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/407
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
The attitude of a satellite placed on a non-heliosynchronous earth orbit in a plane that is inclined relative to the equatorial plane of the earth is controlled for efficient use of solar panels and radiators. The satellite has a structure, solar panels apt to be rotated with respect to the structure rotation and two opposed radiators each fixed on one of two opposed faces of the satellite structure which are orthogonal to the rotation axis. One of the radiators has greater emissivity than the other. A yaw axis bound to the structure satellite and orthogonal to rotation axis is aimed towards the earth. The solar panels of the satellite are maintained in an optimum orientation relative to the sun by rotating them. At least during periods of each year when an angle .beta. between a sun-earth direction and the plane of the satellite orbit lies between two predetermined values, the satellite structure is rotated about the yaw axis to maintain the radiators in a plane parallel to a direction toward the sun so long as the satellite is remote from an orthogonal projection of the sun direction onto the satellite orbit plane. The orientation of the satellite structure is reversed when neces…
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.