대표
청구항
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1. A method for guiding an aircraft during a final approach towards a runway, the method comprising: receiving a geographic position of the aircraft;receiving a geographic position of a runway threshold of the runway;receiving a runway azimuth of the runway;computing a distance from the aircraft to the runway threshold utilizing the geographic position of the aircraft and the geographic position of the runway threshold;computing a bearing to the geographic position of the runway threshold utilizing the geographic position of the aircraft and the geograph...
1. A method for guiding an aircraft during a final approach towards a runway, the method comprising: receiving a geographic position of the aircraft;receiving a geographic position of a runway threshold of the runway;receiving a runway azimuth of the runway;computing a distance from the aircraft to the runway threshold utilizing the geographic position of the aircraft and the geographic position of the runway threshold;computing a bearing to the geographic position of the runway threshold utilizing the geographic position of the aircraft and the geographic position of the runway threshold;projecting the distance from the geographic position of the aircraft to the geographic position of the runway threshold into an along runway component and a cross runway component utilizing the runway azimuth of the runway;determining a distance from the geographic position of the runway threshold to a geographic position of a localizer transmitter;computing a distance geographically along the runway from the geographic position of the aircraft to the geographic position of the localizer transmitter utilizing the distance from the geographic position of the runway threshold to the geographic position of the localizer transmitter;converting an angular localizer deviation into a rectilinear localizer deviation utilizing, in part, the distance along the runway from the geographic position of the aircraft to the geographic position of the localizer transmitter; andproviding the rectilinear localizer deviation to a guidance system for guiding the aircraft during the final approach towards the runway. 2. The method of claim 1, further comprising receiving a runway length of the runway, and wherein: determining the distance from the runway threshold to the localizer transmitter comprises determining the distance from the runway threshold to the localizer transmitter as the runway length; andcomputing the distance from the aircraft to the localizer transmitter comprises computing the distance from the aircraft to the localizer transmitter by adding the distance from the runway threshold to the localizer transmitter to the along runway component of the projection of the distance from the aircraft to the runway threshold. 3. The method of claim 2, wherein the runway length comprises: a standard runway length that is not an actual runway length of the runway; oran actual runway length of the runway. 4. The method of claim 3, wherein computing the distance from the aircraft to the localizer transmitter is performed in accordance with the following equation: dist_to_loc=dist_to_rwy_thd*cos(brg_to_thd−rwy_azmth)+dist_from_rwy_thd_to_loc, wherein dist_to_loc is the distance from the aircraft to the localizer transmitter in an along runway axis, dist_to_rwy_thd is the distance from the aircraft to the runway threshold, brg_to_thd is the bearing to the runway threshold, rwy_azmth is the runway azimuth, and dist_from_rwy_thd_to_loc is the runway length. 5. The method of claim 1, further comprising receiving a geographic position of the localizer transmitter, and wherein: determining the distance from the runway threshold to the localizer transmitter comprises computing the distance from the runway threshold to the geographic position of localizer transmitter; andcomputing the distance from the aircraft to the localizer transmitter comprises computing the distance from the aircraft to the localizer transmitter by adding the distance from the runway threshold to the localizer transmitter to the along runway component of the projection of the distance from the aircraft to the runway threshold. 6. The method of claim 5, wherein computing the distance from the aircraft to the localizer transmitter is performed in accordance with the following equation: dist_to_loc=dist_to_rwy_thd*cos(brg_to_thd−rwy_azmth)+dist_from_rwy_thd_to_loc, wherein dist_to_loc is the distance from the aircraft to the localizer transmitter in an along runway axis, dist_to_rwy_thd is the distance from the aircraft to the runway threshold, brg_to_thd is the bearing to the runway threshold, rwy_azmth is the runway azimuth, and dist_from_rwy_thd_to_loc is the distance from the runway threshold to the localizer transmitter. 7. The method of claim 1, wherein providing the rectilinear localizer deviation to the guidance system comprises providing the rectilinear localizer deviation to an autopilot system of the aircraft, the autopilot system being configured to control the aircraft during the final approach to capture a localizer null of the localizer transmitter; and further comprising: controlling, via the autopilot system, the aircraft during the final approach to capture the localizer null of the localizer transmitter. 8. The method of claim 1, wherein providing the rectilinear localizer deviation to the guidance system comprises providing the rectilinear localizer deviation to a flight director system of the aircraft, the flight director system of the aircraft being configured to provide control instructions to a pilot of the aircraft during the final approach to aid in a capture of a localizer null of the localizer transmitter; and further comprising: providing, via the flight director system, the control instructions to the pilot of the aircraft during the final approach to aid in the capture of the localizer null of the localizer transmitter. 9. An avionics system of an aircraft for guiding the aircraft during a final approach towards a runway, the avionics system comprising: an instrument landing system sensor configured to receive guidance signals from a localizer transmitter during the final approach of the aircraft towards the runway;a navigation system comprising a location component configured to acquire a geographic position of the aircraft,a navigation database configured to store a geographic position of a runway threshold of the runway, a geographic position of a runway threshold of the runway, anda runway azimuth of the runway, and a flight management function configured to receive the geographic position of the aircraft, the geographic position of a runway threshold of the runway, and the runway azimuth of the runway from the navigation database,compute a distance from the geographic position of the aircraft to the geographic position of the runway threshold,compute a bearing to the geographic position of the runway threshold utilizing the geographic position of the aircraft and the geographic position of the runway threshold,project the distance from the geographic position of the aircraft to the geographic position of the runway threshold into an along runway component and a cross runway component utilizing the runway azimuth of the runway,determine a distance from the geographic position of the runway threshold to a geographic position of a localizer transmitter,compute a distance geographically along the runway from the geographic position of the aircraft to the geographic position of the localizer transmitter utilizing the distance from the geographic position of the runway threshold to the geographic position of the localizer transmitter, andprovide the distance from the geographic position of the aircraft to the geographic position of the localizer transmitter to a deviation calculator; andthe deviation calculator being configured to convert an angular localizer deviation into a rectilinear localizer deviation utilizing, in part, the distance along the runway from the geographic position of the aircraft to the geographic position of the localizer transmitter, andprovide the rectilinear localizer deviation to a guidance system for guiding the aircraft during the final approach towards the runway. 10. The avionics system of claim 9, wherein the navigation database is further configured to store a runway length of the runway, and the flight management function is further configured to receive the runway length from the navigation database; and wherein: the flight management function, in being configured to determine the distance from the runway threshold to the localizer transmitter, is configured to determine the distance from the runway threshold to the localizer transmitter as the runway length; andthe flight management function, in being configured to compute the distance from the aircraft to the localizer transmitter, is configured to compute the distance from the aircraft to the localizer transmitter by adding the distance from the runway threshold to the localizer transmitter to the along runway component of the projection of the distance from the aircraft to the runway threshold. 11. The avionics system of claim 10, wherein the runway length comprises: a standard runway length that is not an actual runway length of the runway; oran actual runway length of the runway. 12. The avionics system of claim 11, wherein the flight management function, in being configured to compute the distance from the aircraft to the localizer transmitter, is configured to compute the distance from the aircraft to the localizer transmitter in accordance with the following equation: dist_to_loc=dist_to_rwy_thd*cos(brg_to_thd−rwy_azmth)+dist_from_rwy_thd_to_loc, wherein dist_to_loc is the distance from the aircraft to the localizer transmitter in an along runway axis, dist_to_rwy_thd is the distance from the aircraft to the runway threshold, brg_to_thd is the bearing to the runway threshold, rwy_azmth is the runway azimuth, and dist_from_rwy_thd_to_loc is the runway length. 13. The avionics system of claim 9, wherein the navigation database is further configured to store a geographic position of the localizer transmitter, and the flight management function is further configured to receive the geographic position of the localizer transmitter from the navigation database; and wherein: the flight management function, in being configured to determine the distance from the runway threshold to the localizer transmitter, is configured to compute the distance from the runway threshold to the geographic position of the localizer transmitter; andthe flight management function, in being configured to compute the distance from the aircraft to the localizer transmitter, is configured to compute the distance from the aircraft to the localizer transmitter by adding the distance from the runway threshold to the localizer transmitter to the along runway component of the projection of the distance from the aircraft to the runway threshold. 14. The avionics system of claim 13, wherein the flight management function, in being configured to compute the distance from the aircraft to the localizer transmitter, is configured to compute the distance from the aircraft to the localizer transmitter in accordance with the following equation: dist_to_loc=dist_to_rwy_thd*cos(brg_to_thd−rwy_azmth)+dist_from_rwy_thd_to_loc, wherein dist_to_loc is the distance from the aircraft to the localizer transmitter in an along runway axis, dist_to_rwy_thd is the distance from the aircraft to the runway threshold, brg_to_thd is the bearing to the runway threshold, rwy_azmth is the runway azimuth, and dist_from_rwy_thd_to_loc is the distance from the runway threshold to the localizer transmitter. 15. The avionics system of claim 9, further comprising the guidance system, the guidance system comprising an autopilot system; and wherein: the deviation calculator, in being configured to provide the rectilinear deviation to the guidance system, is configured to provide the rectilinear deviation to the autopilot system; andthe autopilot system being configured to receive the rectilinear localizer deviation from the deviation calculator, andcontrol the aircraft during the final approach to capture a localizer null of the localizer transmitter. 16. The avionics system of claim 9, further comprising the guidance system, the guidance system comprising a flight director system; and wherein: the deviation calculator, in being configured to provide the rectilinear deviation to the guidance system, is configured to provide the rectilinear localizer deviation to the flight director system; andthe flight director system being configured to: receive the rectilinear localizer deviation, andprovide control instructions to a pilot of the aircraft during the final approach to aid in capture of a localizer null of the localizer transmitter. 17. A physical computer storage device having computer readable instructions that, when executed by a computer of an aircraft, cause the computer to: receive a geographic position of the aircraft;receive a geographic position of a runway threshold of a runway;receiving a runway length of the runway;receive a runway azimuth of the runway;compute a distance from the aircraft to the runway threshold utilizing the geographic position of the aircraft and the geographic position of the runway threshold;compute a bearing to the geographic position of the runway threshold utilizing the geographic position of the aircraft and the geographic position of the runway threshold;project the distance from the geographic position of the aircraft to the geographic position of the runway threshold into an along runway component and a cross runway component utilizing the runway azimuth of the runway;compute a distance geographically along the runway from the geographic position of the aircraft to a geographic position of a localizer transmitter by adding the runway length to the along runway component of the projection of the distance from the geographic position of the aircraft to the geographic position of the runway threshold;convert an angular localizer deviation into a rectilinear localizer deviation utilizing, in part, the distance along the runway from the geographic position of the aircraft to the geographic position of the localizer transmitter; andoutput the rectilinear localizer deviation to a guidance system for guiding the aircraft during a final approach towards the runway. 18. The physical computer storage device of claim 17, wherein the runway length comprises: a standard runway length that is not an actual runway length of the runway; or an actual runway length of the runway. 19. The physical computer storage device of claim 17, wherein the guidance system comprises: an autopilot system; ora flight director system. 20. The physical computer storage device of claim 17, wherein the instructions for computing the distance from the aircraft to the localizer transmitter comprise instructions for computing the distance from the aircraft to the localizer transmitter in accordance with the following equation: dist_to_loc=dist_to_rwy_thd*cos(brg_to_thd−rwy_azmth)+rwy_len, wherein dist_to_loc is the distance from the aircraft to the localizer transmitter in an along runway axis, dist_to_rwy_thd is the distance from the aircraft to the runway threshold, brg_to_thd is the bearing to the runway threshold, rwy_azmth is the runway azimuth, and rwy_len is the runway length.
