Passive aircraft monitoring system

• US 5,206,654 A
• Filed: 05/19/1992
• Issued: 04/27/1993
• Est. Priority Date: 05/19/1992
• Status: Expired due to Fees

• Current Assignee: Hughes Aircraft Company (Rtx Corporation)
• Original Assignee: Hughes Aircraft Company (Rtx Corporation)
• Inventors: Lynch, Thomas J., Finkelstein, Marc, Geesaman, Martin J.
• Primary Examiner(s): Blum, Theodore M.
• Application Number:
  US07/886,112
• Time in Patent Office: 343 Days
• Field of Search: 342/410, 342/411, 342/413, 342/418
• US Class Current: 342/410
• 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 11/10 using Doppler effect
• CPC Class Codes: G01S 13/913 for landing purposes

Abstract

A passive aircraft monitoring system (20) receives signals transmitted by an instrument landing system (14, 16) and reflected from aircraft (18). The Doppler shift in the reflected signals is used to calculate the position or velocity of the aircraft. Using the ILS 90 and 150 Hz signals reflected from the aircraft and comparing their magnitude, the altitude and lateral position of the aircraft can also be determined.

Claims

1. A method for monitoring aircraft on a runway approach or departure flight path wherein the aircraft are subject to electromagnetic radiation signals of a landing system, the signals having a known frequency and source comprising:

receiving, at a location offset laterally from the runway, the signals reflected from the aircraft flying along the flight path;

generating digital samples of the reflected signals received by the receiver;

performing a Fourier transform on the digital samples, thereby converting the signals to the frequency domain;

determining the Doppler frequency shift in the converted digital samples; and

calculating an attribute of the aircraft using the Doppler frequency shift of the reflected signals.

2. The method of claim 1 further comprising, after the step of performing a Fourier transform, the step of discriminating signals reflected from different aircraft and wherein the step of calculating the range comprises calculating the range separately for each aircraft.

3. The method of claim 1 wherein the step of calculating an attribute comprises calculating the range of the aircraft using the Doppler frequency shift.

4. The method of claim 3 wherein the step of calculating the range comprises determining the groundspeed of the aircraft and applying the groundspeed to the Doppler frequency shift.

5. A system for monitoring aircraft flying along an Instrument Landing System (ILS) flight path comprising:

a receiver for receiving ILS signals reflected from aircraft flying along the ILS flight path;

an analog to digital converter for generating digital samples of the reflected ILS signals received by the receiver;

a digital signal processor for performing a Fourier transform on the digital samples, converting the signals to the frequency domain; and

a processing unit for determining the Doppler frequency shift in the converted digital samples and calculating an attribute of the aircraft from which the signals are reflected using the Doppler frequency shift.

6. The system of claim 5 wherein the attribute comprises the range of the aircraft.

7. The system of claim 6 wherein the processing unit calculates the range by determining the groundspeed of the aircraft and applies the groundspeed to the Doppler frequency shift.

8. The system of claim 5 wherein the attribute comprises the groundspeed of the aircraft.

9. The system of claim 5 further comprising, a discriminator for discriminating signals reflected from different aircraft and wherein the processing unit calculates the range separately for each aircraft.

10. The system of claim 5 further comprising a switch coupled between the arithmetic unit and the receiver for switching the frequencies to which the receiver is tuned.

11. A method for monitoring aircraft flying along an Instrument Landing System (ILS) flight path comprising:

receiving ILS signals reflected from aircraft flying along the ILS flight path;

generating digital samples of the reflected ILS signals received by the receiver;

performing a Fourier transform on the digital samples, thereby converting the signals to the frequency domain;

determining the Doppler frequency shift in the converted digital samples; and

calculating an attribute of the aircraft using the Doppler frequency shift of the reflected signals.

12. The method of claim 11 wherein the step of calculating an attribute comprises calculating the range of the aircraft using the Doppler frequency shift.

13. The method of claim 12 wherein the step of calculating the range comprises determining the groundspeed of the aircraft and applying the groundspeed to the Doppler frequency shift.

14. The method of claim 13 wherein the step of determining the groundspeed of the aircraft comprises:

receiving ILS marker beacon signals reflected from the aircraft in the ILS flight path;

comparing the times at which the reflected beacon signal are received to determine the aircraft speed between the respective beacon transmitters.

15. The method of claim 11 wherein the step of calculating an attribute comprises calculating the groundspeed of the aircraft using the Doppler frequency shift.

16. The method of claim 11 further comprising, after the step of performing a Fourier transform, the step of discriminating signals reflected from different aircraft and wherein the step of calculating the range comprises calculating the range separately for each aircraft.

17. The method of claim 11 wherein the step of receiving ILS signals comprises receiving reflections of two different frequency components transmitted from a single ILS transmitter.

18. The method of claim 17 wherein the step of discriminating signals comprises searching the converted digital samples for sets of two frequency components having a difference representative of the difference between the two different frequency components transmitted from the single ILS transmitter.

19. The method of claim 17 further comprising the step of comparing the magnitudes of the reflections of the two different frequency components for determining the position of the aircraft with respect to the two signals transmitted from the ILS transmitter.

20. The method of claim 19 wherein the step of comparing comprises comparing the magnitude of the 90 and 150 Hz glide slope transmitter reflections for determining the altitude of the aircraft with respect to the ILS flight path.

21. The method of claim 19 wherein the step of comparing comprises comparing the magnitude of the 90 and 150 Hz localizer transmitter reflections for determining the lateral approach angle of the aircraft with respect to the ILS flight path.

22. A method for determining the groundspeed of aircraft flying along an Instrument Landing System (ILS) flight path comprising:

receiving ILS marker beacon signals reflected from the aircraft in the ILS flight path;

comparing the times at which the reflected beacon signals are received to determine the aircraft speed between the respective beacon transmitters.