SYSTEMS AND METHODS FOR PERFORMING HIGH ACCURATE DISTANCE MEASURING FOR RADAR ALTIMETERS

• US 20060089759A1
• Filed: 02/11/2005
• Published: 04/27/2006
• Est. Priority Date: 10/22/2004
• Status: Abandoned Application

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Becker, Robert C.
• Application Number:
  US10/906,288
• Publication Number:
  US 20060089759A1
• Time in Patent Office: Days
• US Class Current: 701/3
• CPC Class Codes: G01C 23/00 Combined instruments indicating more than one navigational value, e.g. for aircraft; Combined measuring devices for measuring two or more variables of movement, e.g. distance, speed or acceleration

Abstract

Systems and methods for measuring aircraft altitude less than 10 meters. Two signals having different frequencies are simultaneously transmitted. Returns or echos of the two signals are received. The phase of the return of the first and second signals are determined. A distance value based on the determined phase of the first and second return signals is determined.

Claims

1. A method performed on an aircraft, the method comprising:

simultaneously transmitting a signal having different two or more modulating frequencies;

receiving returns of the signal with two modulating frequencies;

determining the phase of the return of the first modulating signal;

determining the phase of the returned second modulating signal; and

determining a distance value based on the determined phase of the first and second return modulating signals.

2. The method of claim 1, further comprising:

determining if the determined distance value is less than a threshold value; and

if the distance value is determined to be less than the threshold value, generating a tail strike warning signal.

3. The method of claim 2, further comprising:

generating at least one of an audio or visual alert, if a tail strike warning signal has been generated.

4. The method of claim 1, further comprising:

controlling aircraft flight operation based on the determined distance value.

5. The method of claim 1, further comprising:

outputting aircraft flight operation control instructions based on the determined distance value.

6. The method of claim 1, wherein the first and second signals are amplitude modulated.

7. The method of claim 6, wherein the wavelength of the first signal is greater than or equal to a predetermined maximum distance range value.

8. The method of claim 7, wherein the wavelength of the second signal is greater than a range uncertainty value for the first signal.

9. The method of claim 8, wherein f₂<

f₁*360/(2*x₁), f₂ is frequency of the second signal, f₁ is frequency of the first signal, and x₁ is a predefined accuracy value of the phase angle measurement for the first signal.

10. An aircraft system comprising:

a transmitter configured to generate a signal having two or more different modulating frequencies;

an antenna configured to simultaneously transmit the generated signals and receive returns of the transmitted signals;

a receiver configured to process the received returns; and

a processing component configured to determine the phase of the return of the first signal modulating, determine the phase of the returned second modulating signal, and determine a distance value based on the determined phase of the first and second return modulating signals.

11. The system of claim 10, further comprising:

a warning component configured to determine if the determined distance value is less than a threshold value, and if the distance value is determined to be less than the threshold value, generating a tail strike warning signal.

12. The system of claim 11, wherein the warning component further is configured to generate at least one of an audio or visual alert, if a tail strike warning signal has been generated.

13. The system of claim 10, further comprising:

a component configured to control aircraft flight operation based on the determined distance value.

14. The system of claim 10, further comprising:

one or more interface devices configured to output aircraft flight operation control instructions based on the determined distance value.

15. The system of claim 10, wherein the first and second signals are amplitude modulated.

16. The system of claim 15, wherein the wavelength of the first signal is greater than or equal to a predetermined maximum distance range value.

17. The system of claim 16, wherein the wavelength of the second signal is greater than a range uncertainty value for the first signal.

18. The system of claim 17, wherein f₂<

f₁*360/(2*x₁), f₂ is frequency of the second signal, f₁ is frequency of the first signal, and x₁ is a predefined accuracy value of the phase angle measurement for the first signal.