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System and method for isolating attitude failures in aircraft

A technology of aircraft and attitude, applied in the direction of control/regulation system, radio wave measurement system, satellite radio beacon positioning system, etc.

Active Publication Date: 2016-05-11
HONEYWELL INT INC
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The cost of maintaining these pools, while smaller than the cost of cancellation or delay, is still significant

Method used

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  • System and method for isolating attitude failures in aircraft
  • System and method for isolating attitude failures in aircraft
  • System and method for isolating attitude failures in aircraft

Examples

Experimental program
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example 1

[0037] Example 1 includes an attitude integrity and display system comprising: a master inertial reference unit that generates a master attitude solution computed at least in part as a function of inertial data from a first navigation stage inertial sensor; coupled to a master inertial a primary aircraft display system of a reference unit, wherein the primary aircraft display system displays a primary attitude solution; a hybrid reference unit that generates a secondary attitude solution calculated at least in part as a function of inertial data from a second navigation stage inertial sensor; coupled to the hybrid an alternate aircraft display system for the reference unit, wherein the alternate aircraft display system displays a secondary attitude solution; an attitude integrity system that generates an attitude integrity (AI) solution calculated from one or more measurements provided by an attitude solution data source, wherein the attitude Scenario data sources provide data ...

example 2

[0038] Example 2 includes the system of example 1, wherein the primary inertial reference unit comprises an air data inertial reference unit (ADIRU).

example 3

[0039] Example 3 includes the system of any of examples 1-2, wherein the hybrid reference unit comprises an air data attitude hybrid reference unit (ADAHRU).

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Abstract

Systems and methods for isolating attitude failures are provided. In one embodiment, an attitude integrity and display system comprises a display system comprising a primary system displaying a first attitude solution and a standby system displaying a second attitude solution;an attitude integrity system generating an attitude integrity (AI) solution calculated from measurements from an attitude solution data source, the AI solution comprising an aircraft roll and pitch, the data source providing data independent from any data generated by inertial sensor flight instruments and not displayed on either the primary or the standby systems; and an attitude monitor that compares the first solution against the second solution. When the first solution deviates from the second solution by more than a threshold, the monitor identifies on the display system which of either the first or the second solution is failed based on which has a greater deviation from the AI solution.

Description

[0001] Cross References to Related Applications [0002] This application is a non-provisional patent application claiming U.S. Provisional Patent Application No. 62 / 065,868, entitled "SYSTEMANDMETHODFORISOLATINGATTITUDEFAILURESINAIRCRAFT," Attorney Docket No. H0047475, filed October 20, 2014 Priority and benefit of , incorporated herein by reference in its entirety. Background technique [0003] In an aircraft, especially a commercial aircraft, there is a minimum configuration of devices required to be operable for the aircraft's departure. For attitude instruments (which provide aircraft pitch and roll indications), the state of the art requires some aircraft types to have two primary and secondary attitude sources for aircraft takeoff. Attitude measurements from the two primary attitude sources are displayed on the main display system, which includes separate screens for the pilot and co-pilot. A secondary or alternate attitude source is displayed on the alternate display...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01C21/00G01C21/16
CPCG01C21/00G01C21/1654G01C23/00B64D45/00G05D1/00B64D43/00G01S19/53G01C9/005
Inventor M·A·阿尔布雷奇特M·R·伊比斯J·R·莫里森
Owner HONEYWELL INT INC
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