Millimeter-wave aircraft landing and taxing system

• US 5,218,360 A
• Filed: 09/17/1992
• Issued: 06/08/1993
• Est. Priority Date: 05/23/1991
• Status: Expired due to Term

• Current Assignee: Northrop Grumman Systems Corporation (Northrop Grumman Corporation)
• Original Assignee: TRW Inc. (Northrop Grumman Corporation)
• Inventors: Peterson, Lee L., Ching, Ronald K., Goetz, Allan C.
• Primary Examiner(s): Issing, Gregory C.
• Application Number:
  US07/946,141
• Time in Patent Office: 264 Days
• Field of Search: 342/407, 342/410, 342/411, 342/414, 342/33, 342/35, 342/195, 342/196
• US Class Current: 342/407
• CPC Class Codes: G01S 1/14 using amplitude comparison of signals transmitted simultaneously from antennas or antenna systems having differently oriented overlapping directivity-characteristics
• CPC Class Codes: G01S 13/913 for landing purposes
• CPC Class Codes: G01S 2013/916 Airport surface monitoring [ASDE]
• CPC Class Codes: G01S 3/28 using amplitude comparison of signals derived simultaneously from receiving antennas or antenna systems having differently-oriented directivity characteristics

Abstract

Apparatus, and a corresponding method, for generating navigational data to aid a pilot in landing or taxiing an aircraft in poor visibility conditions. Radio-frequency (rf) beacons at predetermined locations around an airport runway or taxiway are separately modulated to render them uniquely identifiable from the aircraft. A fixed array of receiving antennas on the aircraft has multiple, angularly spaced antenna beams that substantially overlap each other in coverage, such that a signal received from one of the beacons will in most cases be received in more than one adjacent receive beam. Signals received in each beam are processed by a fast Fourier transform module to separate signal components from the various beacons; then an interpolation process determines the arrival angles of the signals by comparing the amplitudes received in adjacent receive beams. Azimuth and elevation angle values are thereby obtained for each detected beacon, and this information can be used in conjunction with conventionally obtained aircraft attitude and altitude data to produce a visual display for the pilot when landing or taxiing the aircraft.

Claims

1. An aircraft landing or taxiing aid, comprising:

a multiple beam antenna system installed in an aircraft and having overlapping receive beams aligned in different directions to provide coverage of a selected field of view from the aircraft; and

signal processing means, for processing signals received by the multiple beam antenna system, the signal processing means including

signal analysis means, for separating signals from each receive beam into components having amplitudes corresponding to the strengths of signals received from a plurality of emitters installed at known locations on the ground, at least some of the emitters being located to define the outline of a runway, and

angle determination means, for determining the apparent angular location of each detected emitter, whereby the determined angular directions can be used in instruments providing a visual indication of the location and course of the aircraft with respect to the runway;

wherein each emitter is modulated at a different selected frequency, and the signal analysis means includes a fast Fourier transform (FFT) module, to separate the signals from each receive beam into frequency components, thereby uniquely identifying signal contributions from each emitter on the ground, said fast Fourier transform module generating a set of amplitudes for each of the identified emitters, wherein the angle determination means uses the generated amplitudes to determine the angular direction of each emitter.

2. An aircraft landing or taxiing aid as defined in claim 1, and further comprising:

a spherical rf lens positioned in front of the multiple beam antenna system; and

an array of rf processing modules, including means for converting signals received by the antennas into digital form, which is more convenient for signal processing.

3. An aircraft landing or taxiing aid as defined in claim 2, wherein:

each of the rf processing modules includes rf amplifier means, and detector means for converting the rf signals to video signals.

4. An aircraft landing or taxiing aid as defined in claim 1, wherein:

the angle determination means includes means for determining the angular direction of each emitter by interpolating between the alignment angles of adjacent receive beams, based on the amplitudes of signals received in the adjacent receive beams from the same emitter.

5. An aircraft landing or taxing aid as defined in claim 4, wherein:

the angle determination means further includes a lookup table relating a list of ratios of amplitudes of signals received in adjacent receive beams from the same emitter, to a corresponding list of angles, whereby the azimuth angular direction of the emitter can be accurately determined if the emitter signals are received in at least two adjacent azimuth receive beams, and the elevation angular direction can be accurately determined if the emitter signals are received in at least two adjacent elevation beams.

6. An aircraft landing or taxiing aid as defined in claim 1, wherein the signal processing means further includes:

means for calculating the aircraft'"'"'s range from the runway, its deviation from a desired course and its deviation from a desired glideslope, using the determined angles together with measurements of aircraft attitude obtained from conventional instruments.

7. An aircraft landing or taxiing aid as defined in claim 4, and further comprising:

a heads-up display (HUD) for displaying a synthetic image of the runway as viewed from the aircraft.

8. An aircraft landing or taxiing aid as defined in claim 1, wherein:

the multiple beam antenna system includes a two-dimensional array of antenna of rf receive antennas; and

the angle determination means determines the angular locations of the emitters in terms of azimuth angles and elevation angles.

9. An aircraft landing or taxiing system, comprising:

a plurality of radio-frequency (rf) emitters installed at preselected locations on the ground, at least some of the emitters being located to define the outline of a runway;

means for modulating rf signals transmitted by the emitters, such that each emitter is uniquely identifiable by a different selected modulation frequency;

a multiple beam antenna system installed in an aircraft and having overlapping receive beams aligned in different directions to provide coverage of a selected field of view from the aircraft;

a corresponding array of rf processing modules coupled to the multiple beam antenna system, including means for converting any received signals to digital form, in which they may be conveniently processed; and

signal processing means, for further processing signals from the array of rf modules, and including signal analysis means, for separating signals from each rf module into components having amplitudes corresponding to the strengths of signals detected from individual emitters, an further including angle determination means, for determination azimuth and elevation angles of the apparent direction of each detected emitter, whereby the determined azimuth and elevation angles can be used in instruments providing a visual indication of the location and course of the aircraft with respect to the runway;

wherein the signal analysis means includes a fast Fourier transform (FFT) module, to separate the signals from each receive beam into frequency components, thereby uniquely identifying signal contributions from each emitter on the ground, said fast Fourier transform module generating a set of amplitudes for each of the identified emitters, wherein the angle determination means uses the generated amplitudes to determine the angular direction of each emitter.

10. An aircraft landing or taxiing system as defined in claim 9, and further comprising:

a spherical rf lens positioned in front of the array of the multibeam antenna system;

and wherein the rf processing modules convert the received rf signals to video signals.

11. An aircraft landing or taxiing system as defined in claim 10, wherein:

each of the rf processing modules includes rf amplifier means, and detector means for converting the rf signals to video signals.

12. An aircraft landing or taxiing system as defined in claim 11, wherein:

the angle determination means includes means for determining the angular direction of each emitter by interpolating between the alignment angles of adjacent receive beams, based on the amplitudes of signals received in the adjacent receive beams from the same emitter.

13. An aircraft landing or taxiing system as defined in claim 12, wherein:

the angle determination means further includes a lookup table relating a list of ratios of amplitudes of signals received in adjacent receive beams from the same emitter, to a corresponding list of angles, whereby the angular direction of the emitter can be accurately determined if the emitter signals are received in at least two adjacent receive beams.

14. An air landing or taxiing system as defined in claim 9, wherein the signal processing means further includes:

means for calculating the aircraft'"'"'s range from the runway, its deviation from a desired course and its deviation from a desired glideslope, using the determined angles together with measurements of aircraft attitude obtained from conventional instruments.

15. An aircraft landing or taxiing system as defined in claim 14, and further comprising:

a heads-up display (HUD) for displaying a synthetic image of the runway as viewed from the aircraft.

16. A method for providing navigational data to a pilot of an aircraft during landing or taxiing operations, the method comprising the steps of:

emitting a plurality of radio-frequency (rf) signals from beacons at selected locations on the ground, at least some of the beacons being located to define the outline of a runway;

modulating the rf signals transmitted by the beacons, such that each beacon is modulated at a different selected frequency and is uniquely identifiable from an aircraft;

receiving rf signals in the aircraft, using an array of rf antennas having overlapping receive beams aligned in different directions to provide coverage of a selected field of view from the aircraft;

amplifying any received rf signals and converting them to digital form, in which they may be conveniently processed; and

processing the converted signals, the signal processing step including separating converted signals from each rf module into components having amplitudes corresponding to the strengths of signal detected from individual beacons, and determining azimuth and elevation angles of the apparent direction of each detected beacon, whereby the determined azimuth and elevation angles can be used in instruments providing a visual indication of the location and course of the aircraft with respect to the runway;

wherein the step of separating converted signals into components includes performing a fast Fourier transformation (FFT) on the converted signals, to separate them into frequency components, thereby uniquely identifying signal contributions from each beacon on the ground, the step of performing a fast Fourier transform including generating a set of amplitudes for each of the emitters, wherein the step of determining azimuth and elevation angles includes using the generated amplitudes to determine the angular direction of each emitter.

17. A method as defined in claim 16, wherein:

the step of converting converts the received rf signals to video signals.

18. A method as defined in claim 16, wherein:

the step of determining azimuth and elevation angles includes determining the angular direction of each beacon by interpolating between the alignment angles of adjacent receive beams, based on the amplitudes of signals received in the adjacent receive beams from the same beacon.

19. A method as defined in claim 18, wherein:

the determining step further includes accessing a lookup table relating a list of ratios of amplitudes of signals received in adjacent receive beams from the same beacon, to a corresponding list of angles, whereby the angular direction of the beacon can be accurately determined if the emitter signals are received in at least two adjacent receive beams.

20. A method as defined in claim 16, wherein the signal processing step further includes:

calculating the aircraft'"'"'s range from the runway, its deviation from a desired course and its deviation from a desired glideslope, using the determined angles together with measurements of aircraft attitude obtained from conventional instruments.

21. A method as defined in claim 20, and further comprising:

displaying, on a heads-up display (HUD), a synthetic image of the runway as viewed from the aircraft.

22. A method as defined in claim 16, wherein:

least some of the beacons are located to define part of a taxiway;

the method further comprises generating a displayable image of at least one of the beacons defining part of the taxiway, to permit the aircraft to taxi safely in conditions of poor visibility.