SYSTEMS AND METHODS FOR PROVIDING A BAROMETRIC ALTITUDE MONITOR

Abstract

There are provided systems and methods for providing a barometric altitude monitor that assist pilots by providing alerts when a barometric altitude of the ownship aircraft is may be incorrect. Various embodiments of the present invention determine whether significant errors in barometric altitude occur though comparisons to alternate altitude information sources. Through aspects of the present invention, errors arising from manual entry of barometric pressure information by a pilot may be identified before safety issues arise, thus helping to prevent events such as controlled flight into terrain (CFIT).

Claims

1. A method comprising: determining that a barometric altimeter in an ownship aircraft is configured in a mode other than standard (STD) mode; comparing a corrected altitude measurement from the barometric altimeter to a second source of altitude information; and generating an alert if the compared corrected altitude measurement deviates from the second source of altitude information by a predetermined altitude error threshold.

2. The method of claim 1 wherein the second source of information comprises a GPS-determined altitude of the ownship aircraft.

3. The method of claim 1 wherein the second source of information comprises a sum of a radio altitude of the ownship aircraft and a terrain elevation proximate to the ownship aircraft.

4. The method of claim 1 wherein the second source of information comprises altitude measurements received from a transmission from a second aircraft in proximity to the ownship aircraft.

5. The method of claim 1 wherein the second source of information comprises an average of: a GPS-determined altitude of the ownship aircraft; and a sum of a radio altitude of the ownship aircraft and a terrain elevation proximate to the ownship aircraft.

6. The method of claim 1 wherein the second source of information comprises a weighted average of: a GPS-determined altitude of the ownship aircraft; and a sum of a radio altitude of the ownship aircraft and a terrain elevation proximate to the ownship aircraft.

7. The method of claim 1 wherein the predetermined altitude error threshold is selected from a range of plus or minus 0.5% to plus or minus 10% of the corrected altitude measurement.

8. The method of claim 7 wherein the selected altitude error threshold represents the expected error between the barometric altitude source and second source to a 99.999% level of certainty.

9. The method of claim 1 further comprising detecting that an altimeter of the ownship aircraft is configured in Standard (STD) setting; and generating an alert if a radio altitude measurement of the ownship aircraft is less than a predetermined minimum radio altitude threshold.

10. The method of claim 9 wherein the predetermined minimum radio altitude threshold is within a range of 500 feet to 4500 feet.

11. The method of claim 1 further comprising cancelling the alert if the corrected altitude measurement no longer deviates from the second source of altitude information by a predetermined altitude error threshold.

12. The method of claim 9 further comprising cancelling the alert if the radio altitude measurement of the ownship aircraft is greater than or equal to the predetermined minimum radio altitude threshold.

13. A method comprising: determining that a radio altitude measurement of the ownship aircraft is less than a predetermined minimum radio altitude threshold; comparing a corrected altitude measurement from the barometric altimeter to a second source of altitude information; and generating an alert if the compared corrected altitude measurement deviates from the second source of altitude information by a predetermined altitude error threshold.

14. The method of claim 13 wherein the second source of information comprises a GPS-determined altitude of the ownship aircraft.

15. The method of claim 13 wherein the second source of information comprises a sum of a radio altitude of the ownship aircraft and a terrain elevation proximate to the ownship aircraft.

16. The method of claim 13 wherein the second source of information comprises altitude measurements received from a transmission from a second aircraft in proximity to the ownship aircraft.

17. The method of claim 13 wherein the second source of information comprises an average of: a GPS-determined altitude of the ownship aircraft; and a sum of a radio altitude of the ownship aircraft and a terrain elevation proximate to the ownship aircraft.

18. The method of claim 13 wherein the second source of information comprises an average of: a GPS-determined altitude of the ownship aircraft; and a sum of a radio altitude of the ownship aircraft and a terrain elevation proximate to the ownship aircraft.

19. The method of claim 13 wherein the predetermined minimum radio altitude threshold is within a range of 500 feet to 4500 feet.

20. The method of claim 13 wherein the predetermined altitude error threshold is selected from a range of plus or minus 0.5% to plus or minus 10% of the corrected altitude measurement.

21. The method of claim 20 wherein the selected altitude error threshold represents the expected error between the barometric altitude source and second source to a 99.999% level of certainty.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0011] A more complete understanding of the present invention may be derived by referring to the detailed description and claims when considered in connection with the following illustrative figures.

[0012] FIG. 1 illustrates a block diagram of a system embodiment of the present invention.

[0013] FIG. 2 illustrates a flow diagram of an embodiment of the present invention.

[0014] FIG. 3 shows an alternative flow diagram for an embodiment of the present invention.

[0015] FIG. 4 shows a flow diagram of another embodiment of the present invention.

[0016] FIG. 5 shows another flow diagram of another embodiment of the present invention.

DETAILED DESCRIPTION

[0017] Referring to FIG. 1, a system embodiment 100 of the present invention is depicted. The block 101 represents avionic systems disposed within an ownship aircraft, and may incorporate separate components, or may be integrated in whole or in part within a larger system such as a standard Flight Management System or FMS. An embodiment includes a processor 104 electrically coupled to a memory 106, a transceiver 102 electrically coupled to the processor 104; an output device 109, in the cockpit of the ownship aircraft including a display 110 and speaker 112 electrically coupled to the processor 104 (for producing alerts of a visual nature, aural nature, or both) an radio altimeter 120 electrically coupled to the processor 104; a location determination device, for example a GPS device 114, electrically coupled to the processor 104, and a barometric altimeter 130 electrically coupled to the processor 104. The memory 106 may contain a variety of data, such as software programs 44 that may be used in execution of embodiments of the present invention, an operating system 43, altitude/barometric settings and information 45 that stores current barometric measurements and settings (including, optionally, any barometric compensation amounts) and transition altitude 46 that may include a selected transition altitude for the particular region of flight. An antenna 103 that is in signal communication with transceiver 102 receives signals 91, 151, that may comprise ADS-B signals or other aviation-related signals that include altitude information of a second aircraft 150 that is within the local vicinity of the ownship aircraft to further increase accuracy of altitude calculations. For example, nearby aircraft 150 may, as part of its ADS-B transmissions, provide its current altitude or Barometric Pressure Setting (minus 800 millibars), and as the nearby aircraft 150 is proximate to or within the vicinity of the ownship aircraft, its received altitude information may be used as a reference to confirm or identify a discrepancy in the barometric altitude measurement of the ownship aircraft. Further, altitude measurements of either the ownship aircraft or second aircraft 150 may be received from a ground station 90 and used for confirmation of current barometric altitude of the ownship aircraft.

[0018] Embodiments of the present invention may monitor the barometric mode setting from the aircraft, and as such, FIG. 2 illustrates an embodiment of a process 200 of the present invention. A determination is made 205 whether the barometric mode setting of the aircraft's altimeter is set to a mode other than Standard or STD, and if so, the process may monitor the apparent accuracy of the barometric corrected altitude 210. The corrected altitude may be compared to GPS/geolocation altitude, as well as the sum of radio altitude and the terrain elevation, or an average of the GPS and combined radio plus terrain altitude measurements. If the corrected altitude is not consistent with the other measurements of aircraft altitude, then an alert may be provided 215 to the pilot. For example, in an embodiment a comparison is made between a corrected altitude measurement from the barometric altimeter to a second source of altitude information (such as a geolocation/GPS altitude, or a radio altitude plus altitude above terrain), and an alert is generated if the compared corrected altitude measurement deviates from the second source of altitude information by a predetermined altitude error threshold. The predetermined altitude error threshold may be determined by any desired technique, such as by plus or minus 3% of the corrected altitude measurement, or a fixed altitude range. If the aircraft is indicating STD mode 205 or if there is no detected significant error in the corrected barometric altitude 210, an alert may be cancelled 220 if active.

[0019] In various embodiments, an altitude error threshold may be a statistically derived threshold. Such a threshold would be dynamic and depend on multiple factors. For example, in one scenario, if it is known that statistically speaking, the real atmosphere varies from an idealized atmospheric model by an amount that depends on altitude and air temperature, aspects of the invention can quantify how much error in the barometric altitude is reasonable/probable given the known model and the actual atmospheric variations. Further, if an altitude calculated based on the ambient pressure and assuming an idealized atmosphere is on average correct, and may have a standard variation (or in some embodiments, standard deviation) such that the calculation is may provide a range of 6 feet per 100 feet of altitude. Thus, a one sigma error due to altitude would be 6 feet per 100 feet. Further, in various embodiments, to estimate how large of an error could be expected at the 95th percentile, embodiments could calculate 1.96 times the sigma error (i.e., 1.96 sigma equates to 95% when there is normal or Gaussian distribution). Similarly, embodiments could calculate a 99.9% expected error as 3.3 times sigma or a 99.999% expected error as 4.4 times sigma.

[0020] In addition to the expected error that is a function of altitude, for various embodiments, there may be an altitude error threshold that is a function of temperature. In this embodiment, the further the atmospheric temperature at a given attitude is from standard, the larger the altitude error might be. For example, in one aspect, for every degree Celsius of temperature deviation from standard temperature, the standard deviation of altitude error is 10 feet. Thus, when the atmospheric temperature is 10 deg C warmer than standard, the temperature-based sigma would be 100 feet. Here again aspects of the present invention could calculate a 4.4 sigma value to determine the altitude error that could be expected at the 99.999 percentile.

[0021] In additional embodiments, other error sources could similarly be characterized. Additional error sources include not only error sources in the barometric altitude, but errors in the truth source, such as GPS. For instance, VFOM gives a 95% (1.96 sigma) vertical error estimate for GPS. Thus, embodiments could calculate a 4.4 sigma error for GPS based on that estimate.

[0022] Additionally, an overall expected error could then be calculated by root-sum-squaring the various errors. The resulting value would be the threshold that could be used to trigger an alert. For instance, if the difference between the barometric altitude and the GPS altitude is 150 feet and the 99.999% expected error is 149 feet, the system could determine, with 99.999% confidence, that the difference between the barometric altitude and the GPS altitude was due to something other than reasonably expected inaccuracies in the barometric and GPS altitudes; this would be the point when an alert would be generated.

[0023] FIG. 3 illustrates another embodiment of a process 300 of the present invention. In one aspect of this embodiment, similarly to the process shown in FIG. 2, a check is made 305 as to whether the barometric altimeter of the ownship aircraft is operating when the aircraft is not in STD mode, and if not, the reasonableness of barometric corrected altitude may be measured 310 by comparing it to a secondary altitude source, such as geolocation/GPS altitude, or the sum of radio altitude and the terrain elevation, or an average of these values. If the corrected altitude is not consistent with the other two measurements of aircraft altitude, then an alert 315 may be provided to the pilot. Additionally, if the process detects 305 that the altimeter is still in STD setting and the radio altitude is less than a set threshold 320, the process may generate an alert 325 to the flight crew. This alert may be based on the fact that once the aircraft is relatively close to terrain, STD may not be the proper setting. Relative closeness to terrain may be determined by any desired method; in one embodiment, relative closeness to terrain may be determined by radio altitude being less than a predetermined distance such as 1500 feet or in a range of 500 feet to 4500 feet, an alert may be produced. If neither a significant error in the corrected barometric altitude is detected 310 nor the radio altitude is found to be unusually small for STD mode 320, alerts are cancelled if currently active, i.e., once the triggering condition is corrected.

[0024] FIG. 4 illustrates yet another embodiment of a process 400 of the present invention. In this embodiment, a process of the present invention may check 405 to see if the radio altitude reading is below a certain threshold, indicating that the aircraft may be relatively close to terrain. When the radio altitude is sufficiently small, the process may compare 410 the barometric corrected altitude to a secondary source of altitude, such as the geolocation/GPS altitude, as well as the sum of radio altitude and terrain elevation. If the corrected altitude is not consistent with the other secondary measurements of aircraft altitude, then an alert 415 may be provided to the pilot. If conditions 405, 410 are determined negatively, alerts are cancelled 420 if they were currently activated.

[0025] FIG. 5 illustrates a further embodiment of a process 500 of the present invention. As mentioned above, transmissions from nearby aircraft, such as ADS-B transmissions, may provide a secondary source of information regarding barometric altitude information, and more particularly, to confirm the accuracy of ownship's barometric altimeter setting. A process of the present invention obtains 510 transmissions from a nearby aircraft, or a plurality of nearby aircraft, and may and may respectively decode such transmissions to obtain respective barometric altitude information for each of the nearby transmitting aircraft, which further comprises a barometric altimeter setting (e.g. 29.55 inches of mercury). The barometric altimeter setting, whether a single value for a single nearby aircraft, or a plurality of values for a plurality of nearby aircraft, may be compared 513 to the current barometric altimeter setting of the ownship aircraft to determine whether a significant amount of discrepancy exists between ownship's barometric altimeter setting and nearby aircraft's reported barometric altimeter settings. If the difference between ownship's barometric altimeter setting and a single value of barometric altimeter setting corresponding to the single nearby aircraft exceeds a predetermined threshold (for example, but not by way of limitation, more than 0.5 inches mercury or 17 millibars, although larger values may be utilized such as 1 inch mercury or 34 millibars), then an alert 515 may be provided to the pilot. Similarly, if the difference between ownship's barometric altimeter setting and an average of a plurality of barometric altimeter settings corresponding to a plurality of nearby aircraft exceeds a predetermined for example, but not by way of limitation, more than 0.5 inches mercury or 17 millibars, although larger values may be utilized such as 1 inch mercury or 34 millibars), then an alert 515 may be provided to the pilot. If condition 513 is determined negatively, an alert may be cancelled 520 if it was currently activated.

[0026] The particular implementations shown and described above are illustrative of the invention and its best mode and are not intended to otherwise limit the scope of the present invention in any way. Indeed, for the sake of brevity, conventional data storage, data transmission, and other functional aspects of the systems may not be described in detail. Methods illustrated in the various figures may include more, fewer, or other steps. Additionally, steps may be performed in any suitable order without departing from the scope of the invention. Furthermore, the connecting lines shown in the various figures are intended to represent exemplary functional relationships and/or physical couplings between the various elements. Many alternative or additional functional relationships or physical connections may be present in a practical system.

[0027] Changes and modifications may be made to the disclosed embodiments without departing from the scope of the present invention. These and other changes or modifications are intended to be included within the scope of the present invention, as expressed in the following claims.