Systems and methods for attitude fault detection based on integrated GNSS/inertial hybrid filter residuals
US9593962B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 9, 2014 |
| Grant date | Mar 14, 2017 |
| Priority date | — |
| Expiry date | Apr 19, 2036 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG07C5/0808
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
Systems and methods for attitude fault detection based on integrated GNSS/inertial hybrid filter residuals are provided. In one embodiment, a fault detection system for aircraft attitude measurement system comprises: a sensor monitor coupled to a first inertial measurement unit, the sensor monitor comprising: a navigation error model for the first inertial measurement unit, the model configured to model a plurality of error states including at least an attitude error state vector, an velocity error state vector, and a position error state vector determined from data generated by the first inertial measurement unit; and a propagator-estimator configured to propagate and update error states based on GNSS data; and a residual evaluator configured to input measurement error residual values generated by the propagator-estimator, wherein the residual evaluator outputs an alert signal when the measurement error residual values exceed a threshold.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.