[특허]Method of detecting attitude faults based on magnetometer measurements

Honeywell International Inc.

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특허 상세정보

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내보내기 페이스북 공유 트위터 공유 카카오톡 공유

Method of detecting attitude faults based on magnetometer measurements

특허상세정보
국가/구분	United States(US) Patent 등록
국제특허분류(IPC7판)	G01C-009/00 B64D-045/00 G01S-019/40 B64D-043/00 G01C-017/38 G01C-021/08 G01C-021/16
출원번호	US-0599027 (2015-01-16)
등록번호	US-9719782 (2017-08-01)
발명자 / 주소	Morrison, John R. Weed, Douglas Mark Hickey, Mark
출원인 / 주소	Honeywell International Inc.
대리인 / 주소	Fogg & Powers LLC
인용정보	피인용 횟수 : 0 인용 특허 : 7

초록
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An avionics system comprises one or more attitude sources, each configured to produce a respective calculated attitude solution; at least one magnetometer configured to measure magnetic field; and at least one attitude monitor configured to use the respective calculated attitude solution from one of the attitude sources to project the measured magnetic field estimate or an Earth Magnetic Field Model (EMFM) estimate such that the measured magnetic field estimate and the EMFM estimate are in a common shared frame. The at least one attitude monitor is further configured to determine a difference between the measured magnetic field estimate and the EMFM estimate in the common shared frame. The at least one attitude monitor is further configured to output an alert, which indicates that the respective calculated attitude solution used to project the measured magnetic field estimate or the EMFM estimate is in error, if the difference exceeds a predetermined threshold.

대표
청구항
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1. An avionics system comprising: one or more attitude sources, each configured to produce a respective calculated attitude solution;at least one magnetometer configured to measure magnetic field in a frame of the avionics system and provide the measurement as a measured magnetic field estimate; andat least one attitude monitor configured to use the respective calculated attitude solution from at least one of the one or more attitude sources to project at least one of the measured magnetic field estimate or an Earth Magnetic Field Model estimate such that the measured magnetic field estimate and the Earth Magnetic Field Model estimate are in a common shared frame;wherein the at least one attitude monitor is further configured to determine a respective difference between the measured magnetic field estimate and the Earth Magnetic Field Model estimate in the common shared frame;wherein the at least one attitude monitor is further configured to output an alert, which indicates that the respective calculated attitude solution used to project at least one of the measured magnetic field estimate or the Earth Magnetic Field Model estimate is in error, when the respective difference between the measured magnetic field estimate and the Earth Magnetic Field Model estimate exceeds a predetermined threshold; andwherein the at least one attitude monitor is configured to provide an indication that the difference between the measurement magnetic field estimate and the Earth Magnetic Field Model estimate is not valid when an attitude sensitivity level of the at least one attitude monitor is less than the predetermined threshold. 2. The avionic system of claim 1, wherein the at least one attitude monitor is further configured to determine when the attitude sensitivity level of the at least one attitude monitor exceeds the predetermined threshold. 3. The avionics system of claim 2, wherein the one or more attitude sources comprises a plurality of attitude sources, each of the plurality of attitude sources configured to provide a respective measured magnetic field estimate; wherein the at least one attitude monitor is further configured to determine when a difference between the Earth Magnetic Field Model estimate and the respective measured magnetic field estimate of one of the plurality of attitude sources exceeds the predetermined threshold more than a respective difference between the Earth Magnetic Field Model estimate and the respective measured magnetic field estimate of the other attitude sources;wherein the at least one attitude monitor is configured to indicate that the attitude source, for which the difference exceeds the predetermined threshold more than the respective differences for the other attitude sources, is faulted. 4. The avionics system of claim 1, wherein the one or more attitude sources comprises a plurality of attitude sources; and wherein the at least one monitor comprises a plurality of monitors, each of the plurality of monitors corresponding to a respective one of the plurality of attitude sources. 5. The avionics system of claim 4, wherein each of the plurality of attitude monitors is integral to a respective one of the plurality of attitude sources. 6. The avionics system of claim 1, further comprising a position sensor configured to provide position data to the at least one attitude monitor, the at least one attitude monitor configured to determine the Earth Magnetic Field Model estimate based, at least in part, on the position data. 7. The avionics system of claim 6, wherein the position sensor is one of a Global Navigation Satellite System receiver or an Inertial Reference System. 8. The avionics system of claim 1, wherein each of the one or more attitude sources comprises one of an Air Data Inertial Reference Unit (ADIRU), an Inertial Reference Unit (IRU), or an Attitude Heading Reference Unit (AHRU). 9. The avionics system of claim 1, wherein at least one of the one or more attitude sources is configured to provide position data to the at least one attitude monitor, the at least one attitude monitor configured to determine the Earth Magnetic Field Model estimate based, at least in part, on the position data. 10. The avionics system of claim 1, wherein the common shared frame is one of the frame of the avionics system or the reference frame of the Earth Magnetic Field Model estimate. 11. A method of monitoring attitude faults in an avionics system, the method comprising: obtaining an attitude solution;obtaining a geographic position of the avionics system;obtaining a measured magnetic field estimate in a frame of the avionics system;computing an Earth Magnetic Field Model (EMFM) estimate in a reference frame based, at least in part, on the geographic position of the avionics system;transforming at least one of the measured magnetic field estimate or the EMFM estimate based on the attitude solution such that the measured magnetic field estimate and the EMFM estimate are in a common shared frame;determining when a difference between the measured magnetic field estimate and the EMFM estimate in the common shared frame exceeds a predetermined threshold;when the difference exceeds the predetermined threshold, outputting an alert indicating that the attitude solution is in error; andproviding an indication that the difference between the measurement magnetic field estimate and the Earth Magnetic Field Model estimate is not valid when an attitude error sensitivity level is less than the predetermined threshold. 12. The method of claim 11, wherein obtaining the geographic position comprises obtaining the geographic position from one of a position sensor or an attitude source which generates the attitude solution. 13. The method of claim 12, wherein obtaining the geographic position from a position sensor comprises obtaining the geographic position from a Global Navigation Satellite System receiver. 14. The method of claim 11, wherein the common shared frame is one of the frame of the avionics system or the reference frame of the EMFM estimate. 15. The method co claim 11, further comprising: determining when the attitude error sensitivity level is greater than the predetermined threshold. 16. A program product comprising a non-transitory processor-readable medium on which program instructions are embodied, wherein the program instructions are configured, when executed by at least one programmable processor, to cause the at least one programmable processor to: receive a measured magnetic field estimate in a frame of an avionics system;compute an Earth Magnetic Field Model (EMFM) estimate in a reference frame based, at least in part, on a geographic position of the avionics system;transform at least one of the received measured magnetic field estimate or the EMFM estimate based on an attitude solution received from an attitude source such that the measured magnetic field estimate and the EMFM estimate are in a common shared frame;determine when a difference between the measured magnetic field estimate and the EMFM estimate in the common shared frame exceeds a predetermined threshold;output an alert indicating that the attitude solution is in error when the difference exceeds the predetermined threshold; andoutput an indication that the difference between the measurement magnetic field estimate and the Earth Magnetic Field Model estimate is not valid for determining whether the attitude solution is in error when an attitude error sensitivity level is less than the predetermined threshold. 17. The program product of claim 16, wherein the program instructions are further configured to cause the at least one programmable processor to obtain the geographic position from a position sensor. 18. The program product of claim 16, wherein the common shared frame is one of the frame of the avionics system or the reference frame of the EMFM estimate; and wherein the program instructions are further configured to cause the at least one programmable processor to transform the measured magnetic field estimate to the reference frame of the EMFM estimate or to transform the EMFM estimate to the frame of the avionics system. 19. The program product of claim 16, wherein the program instructions are further configured to cause the at least one programmable processor to determine when an attitude sensitivity level exceeds the predetermined threshold. 20. The program product of claim 16, wherein the program instructions are further configured to cause the at least one programmable processor to: determine when the attitude error sensitivity level is greater than the predetermined threshold.

이 특허에 인용된 특허 (7)

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Method of detecting attitude faults based on magnetometer measurements

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Method of detecting attitude faults based on magnetometer measurements

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