Systems and methods for attitude fault detection based on air data and aircraft control settings
US9435661B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 9, 2014 |
| Grant date | Sep 6, 2016 |
| Priority date | — |
| Expiry date | Dec 9, 2034 |
Classification
- Technology area (CPC G)Physics
- CPC primaryG07C5/0808
- WIPO fieldControl
- WIPO sectorInstruments
Abstract
Systems and methods for attitude fault detection based on air data and aircraft control settings are provided. In one embodiment, a sensor monitor for an aircraft attitude measurement system comprises: an aircraft model configured to model a plurality of states, the plurality of states including at least an aircraft attitude state, an aircraft velocity state, a sink rate error state, and a wind velocity state; a propagator-estimator configured to utilize the plurality of states of the aircraft model to process air data measurements and attitude measurements from a first inertial measurement unit of the aircraft attitude measurement system; and a residual evaluator configured to input residual error values generated by the propagator-estimator, wherein the residual evaluator outputs an alert signal when the residual error values exceed a predetermined statistical threshold.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.