Synthesized attitude and heading inertial reference
US5841537A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Aug 11, 1997 |
| Grant date | Nov 24, 1998 |
| Priority date | — |
| Expiry date | Aug 11, 2017 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG01C21/166
- WIPO fieldMeasurement
- WIPO sectorInstruments
Abstract
An inertial reference system for determining the attitude and rate of change of attitude of a vehicle such as an aircraft is disclosed. Redundancy of the inertial reference system may be accomplished by replacement of one of the fiber optic gyroscopes of an otherwise dual fiber optic gyros installation with a low-cost reference IMU. Failure detection and isolation of a fiber optic gyroscope system may be accomplished with a low-cost reference IMU rather than with an additional fiber optic gyroscope. The information provided by the eliminated fiber optic gyroscope is synthesized from the output of the remaining fiber optic gyroscope and the output of the low-cost reference IMU.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.