Method of controlling the attitude of satellites, particularly agile satellites with a reduced number of gyrodynes
US7661627B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Oct 29, 2004 |
| Grant date | Feb 16, 2010 |
| Priority date | — |
| Expiry date | Jan 14, 2025 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G1/32
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A method of controlling the attitude of a satellite (1) including two gyrodynes (3,4) and a third main actuator (2) which delivers torques at least along the Z axis. The method includes: fixing the gimbal axes, A1 and A2, of the gyrodynes (3, 4) parallel to Z; setting a non-zero bias (α) between the angular momentum vectors (Formula I) of the gyrodynes; using the measurements provided by the sensors on board the satellite to estimate the kinematic and dynamic variables necessary in order to control the attitude of the satellite (1); calculating set variables in order to the objectives assigned to the satellite (1) attitude control system; and using the deviations between the estimated variables and the set variables to calculate control orders and to send same to the main actuators (2, 3, 4).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.