Three-axis inertial attitude determination for spinning spacecraft
US6282467A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Oct 14, 1997 |
| Grant date | Aug 28, 2001 |
| Priority date | — |
| Expiry date | Oct 14, 2017 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64G3/00
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A system and method for determining the attitude in an inertial frame of a spacecraft spinning about an axis in a body frame including determining momentum vector direction in the inertial frame; determining momentum vector direction in the body frame; acquiring information from an at least single-axis sensor; obtaining reference information on the at least single-axis sensor; updating the attitude in the inertial reference frame using the momentum vector direction in the inertial frame, the momentum vector direction in the body frame, the output of the at least single-axis sensor, and the reference information on the at least single-axis sensor; and propagating the attitude using data from one or more inertial sensors.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.