[특허]System and method for isolating attitude failures in aircraft

Honeywell International Inc

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특허 상세정보

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System and method for isolating attitude failures in aircraft

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	B64D-043/00 B64D-045/00 G01S-019/53 G01C-009/00 G01C-021/16 G01C-023/00
출원번호	US-0575762 (2014-12-18)
등록번호	US-9688416 (2017-06-27)
발명자 / 주소	Ahlbrecht, Mark A. Ibis, Michael R. Morrison, John R.
출원인 / 주소	Honeywell International Inc
대리인 / 주소	Fogg & Powers LLC
인용정보	피인용 횟수 : 0 인용 특허 : 16

초록
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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.

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1. An attitude integrity and display system, the system comprising: a primary inertial reference unit generating a primary attitude solution calculated at least in part as a function of inertial data from a first navigation-grade inertial sensor;a primary aircraft display system coupled to the primary inertial reference unit, wherein the primary aircraft display system displays the primary attitude solution;a hybrid reference unit comprising a first processor that generates a secondary attitude solution calculated at least in part as a function of inertial data received by the first processor from a second navigation-grade inertial sensor;a standby aircraft display system coupled to the hybrid reference unit, wherein the standby aircraft display system displays the secondary attitude solution;an attitude integrity system comprising a second processor that generates an attitude integrity (AI) solution calculated by one or more measurements provided to the second processor by an attitude solution data source, wherein the attitude solution data source provides data independent from the first navigation-grade inertial sensor and the second navigation-grade inertial sensor, wherein the attitude integrity solution is not displayed on either the primary aircraft display system or the standby aircraft display system;an attitude monitor comprising a third processor coupled to the attitude integrity system, wherein the attitude monitor includes a monitoring mode in which the attitude monitor compares the primary attitude solution against the secondary attitude solution;wherein when the primary attitude solution deviates from the secondary attitude solution by more than a predetermine threshold, the attitude monitor identifies either the primary attitude solution or the secondary attitude solution as a failed solution based on a determination of which of the primary attitude solution or the secondary attitude solution has a greatest deviation from the attitude integrity solution; andwherein the attitude monitor generates a warning on one or both of the primary or standby aircraft display system identifying the failed solution. 2. The system of claim 1, wherein the primary inertial reference unit comprises an air data inertial reference unit (ADIRU). 3. The system of claim 1, wherein the hybrid reference unit comprises an air data attitude hybrid reference unit (ADAHRU). 4. The system of claim 1, wherein the hybrid reference unit comprises a first processor and a second processor, wherein the secondary attitude solution is calculated by an attitude and heading reference system (AHRS) implemented on the first processor; and wherein the attitude integrity system is implemented on the second processor. 5. The system of claim 4, wherein the AI solution is communicated by the second processor to the first processor, wherein the first processor bundles the AI solution together in one or more packets with the secondary attitude solution and communicates the one or more packets to the attitude monitor. 6. The system of claim 1, wherein the attitude solution data source provides one or more of: inertial measurements, magnetometer measurements, global navigation satellite system (GNSS) measurements, air data measurements, or combinations thereof. 7. The system of claim 1, wherein the attitude monitor enters the monitoring mode when the primary inertial reference unit is an only remaining in-service primary inertial reference unit of a plurality of primary inertial reference units. 8. The system of claim 1, wherein when the primary attitude solution deviates from the secondary attitude solution by more than a predetermine threshold, but the attitude monitor has not yet identified the failed solution the attitude monitor generates a warning indicating that a miscompare exists between attitude solutions. 9. The system of claim 1, wherein when the primary attitude solution deviates from the secondary attitude solution by more than a predetermine threshold, the attitude monitor generates guidance identifying a specific aircraft maneuver for the pilot to perform. 10. An attitude integrity and display system for an aircraft, the system comprising: a display system comprising a primary aircraft display system for displaying a first attitude solution and a standby aircraft display system for displaying a second attitude solution;an attitude integrity system comprising a first processor that generates an attitude integrity (AI) solution calculated from one or more measurements provided to the first processor by an attitude solution data source, the AI solution comprising an aircraft roll measurement and an aircraft pitch measurement, wherein the attitude solution data source provides data independent from any data generated by inertial sensor flight instruments aboard the aircraft, and wherein the AI solution is not displayed on either the primary aircraft display system or the standby aircraft display system; andan attitude monitor coupled to the attitude integrity system and comprising a second processor that compares the first attitude solution against the second attitude solution, wherein when the first attitude solution deviates from the second attitude solution by more than a threshold, the attitude monitor identifies on the display system which of either the first attitude solution or the second attitude solution is a failed solution based on which of the first attitude solution or the second attitude solution has a greater deviation from the attitude integrity solution. 11. The system of claim 10, wherein the first attitude solution is generated by an air data inertial reference unit (ADIRU). 12. The system of claim 10, wherein the second attitude solutions is generated by an air data attitude hybrid reference unit (ADAHRU). 13. The system of claim 10, wherein when the first attitude solution deviates from the second attitude solution by more than a predetermine threshold but has not yet identified which of either the first attitude solution or the second attitude solution is a failed solution, the attitude monitor displays first displays a warning indicating a miscompare exists between attitude solutions. 14. The system of claim 10, wherein the attitude solution data source provides one or more of: inertial measurements, magnetometer measurements, global navigation satellite system (GNSS) measurements, air data measurements, or combinations thereof. 15. The system of claim 10, wherein when the first attitude solution deviates from the second attitude solution by more than a predetermine threshold, the attitude monitor displays guidance identifying a specific aircraft maneuver for the pilot to perform. 16. A method for identifying a failed attitude solution on an aircraft having a primary aircraft display system for displaying a first attitude solution and a standby aircraft display system for displaying a second attitude solution, the method comprising: generating an attitude integrity (AI) solution calculated from one or more measurements provided by an attitude solution data source, the AI solution comprising an aircraft roll measurement and an aircraft pitch measurement, wherein the attitude solution data source provides data independent from any navigation data generated by inertial sensor flight instruments aboard the aircraft, wherein the AI solution is not displayed on either the primary aircraft display system or the standby aircraft display system;comparing the first attitude solution against the second attitude solution;wherein when the first attitude solution deviates from the second attitude solution by more than a threshold, identifying which of either the first attitude solution or the second attitude solution is a failed solution based on which of the first attitude solution or the second attitude solution has a greatest deviation from the attitude integrity solution. 17. The method of claim 16, wherein the first attitude solution is a primary attitude solution generated by an air data inertial reference unit (ADIRU). 18. The method of claim 16, wherein the second attitude solution is a secondary attitude solution generated by an air data attitude hybrid reference unit (ADAHRU). 19. The method of claim 16, wherein when the first attitude solution deviates from the second attitude solution by more than a predetermine threshold but has not yet identified which of either the first attitude solution or the second attitude solution is a failed solution, the method further comprises displaying a warning indicating a miscompare exists between attitude solutions. 20. The method of claim 16, wherein the attitude solution data source provides one or more of: inertial measurements, magnetometer measurements, global navigation satellite system (GNSS) measurements, air data measurements, or combinations thereof.

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System and method for isolating attitude failures in aircraft

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