Air traffic advisory system bearing estimation receiver

• US 5,604,504 A
• Filed: 08/24/1995
• Issued: 02/18/1997
• Est. Priority Date: 08/24/1995
• Status: Expired due to Term

• Current Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Original Assignee: Alliedsignal Inc. (Honeywell International Inc.)
• Inventors: Nail, David L.
• Primary Examiner(s): Issing, Gregory C.
• Application Number:
  US08/518,934
• Time in Patent Office: 544 Days
• Field of Search: 342/424, 342/152, 342/149, 342/427, 342/147, 342/153, 342/454, 342/417, 342/442, 342/29
• US Class Current: 342/417
• CPC Class Codes: G01S 13/933 of aircraft or spacecraft
• CPC Class Codes: G01S 3/10 Means for reducing or compensating for quadrantal, site, or like errors
• CPC Class Codes: G01S 3/32 derived from different combinations of signals from separate antennas, e.g. comparing sum with difference

Abstract

In an air traffic advisory system for determining the bearing of an intruder aircraft relative to a protected aircraft, the preferred apparatus determines a corrected bearing to compensate for bearing errors caused by intruder signal reflections. More particularly, the preferred apparatus uses a hybrid combiner to produce a sum, delta one and delta two signals, and determines the phase relationship between the sum signal and each of the delta signals, the two phase relationships being subject to at least partially offsetting errors due to intruder signal reflections. The apparatus determines an uncorrected intruder bearing from each phase relationship and then averages the uncorrected bearings to produce a corrected intruder bearing.

Claims

1. In a traffic advisory system wherein an intruder aircraft is equipped for transmitting intruder signals and wherein a protected aircraft is equipped for receiving the intruder signals and determining therefrom the intruder bearing as the bearing angle of the intruder aircraft relative to the protected aircraft, the intruder bearing being subject to error, an apparatus for determining a corrected intruder bearing, said apparatus comprising:

an array of antennas mounted aboard the protected aircraft, said antennas being operable for receiving the intruder signals and responsive thereto for producing respective antenna signals; and

signal processing means for receiving and processing said antenna signals for determining the bearing of the intruder aircraft relative to the protected aircraft, said signal processing means including

signal combining means including means for producing a sum signal representative of the sum of selected antenna signals, and means for producing a first delta signal representative of the differences of selected antenna signals,

receiving means for producing a first phase signal representative of the phase relationship between said sum and first delta signals, said first phase signal being representative of a first intruder bearing and being subject to error due to intruder signal reflection,

said signal combining means including means for producing a second delta signal representative of the differences of selected antenna signals,

said receiving means including means for producing a second phase signal representative of the phase relationship between said sum and second delta signals, said second phase signal being representative of a second intruder bearing and being subject to error due to intruder signal reflection,

said signal combining means including means for producing said first and second delta signals so that said errors of said first and second phase signals are at least partially offsetting,

said signal processing means further including bearing determining means for determining a corrected bearing as a function of both said first and second phase signals.

2. The apparatus as set forth in claim 1, said antenna array including four of said antennas.

3. The apparatus as set forth in claim 2, the protected aircraft presenting a heading axis, two of said antennas being positioned on one side of said axis and the other two of said antennas being positioned on the opposed side of said axis.

4. The apparatus as set forth in claim 2, said antenna array including four of said antennas producing respective antenna signals as signals A, B, C and D.

5. The apparatus as set forth in claim 4, said sum signal being represented by A+B+C+D.

6. The apparatus as set forth in claim 4, said first delta signal being represented as A-jB-C+jD where j represents a phase shift of 90°

.

7. The apparatus as set forth in claim 4, said second delta signal being represented as A+jB-C-jD where j represents a phase shift of 90°

.

8. The apparatus as set forth in claim 1, said bearing determining means including means for deriving a first intruder bearing as a function of said first phase signal, for deriving a second intruder bearing as a function of said second phase signal, and for determining said corrected bearing as the average of said first and second intruder bearings.

9. The apparatus as set forth in claim 1, said signal combining means including a hybrid combiner.

10. The apparatus as set forth in claim 9, said apparatus including a housing enclosing said hybrid combiner and said array, said hybrid combiner and said array being positioned within said housing.

11. The apparatus as set forth in claim 1,

said antennas producing said respective antenna signals as signals A, B, C and D, said sum signal being represented by A+B+C+D, said first delta signal being represented as A+jB-C-jD, said second delta signal being represented as A-jB-C+jD, where j represents a phase shift of 90°

, and

said bearing determining means including means for deriving a first intruder bearing as a function of said first phase signal, for deriving a second intruder bearing as a function of said second phase signal, and for determining said corrected bearing as the average of said first and second intruder bearings.

12. The apparatus as set forth in claim 1, said receiving means including a first channel for processing said sum signal, a second channel for processing said delta signals, and a switch between said array and said second channel for alternately providing said first and second delta signals to said second channel.

13. The apparatus as set forth in claim 1, said signal combining means including a hybrid combiner having a plurality of hybrid couplers.

14. The apparatus as set forth in claim 1,

said signal combining means including a hybrid combiner, said apparatus including a housing enclosing said array, said hybrid combiner being positioned within said housing,

said antenna array including four of said antennas, the protected aircraft presenting a heading axis, two of said antennas being positioned on one side of said axis and the other two of said antennas being positioned on the opposed side of said axis,

said antennas producing said respective antenna signals as signals A, B, C and D, said sum signal being represented by A+B+C+D, said first delta signal being represented as A+jB-C-jD, said second delta signal being represented as A-jB-C+jD, where j represents a phase shift of 90°

, and

said bearing determining means including means for deriving a first intruder bearing as a function of said first phase signal, for deriving a second intruder bearing as a function of said second phase signal, and for determining said corrected bearing as the average of said first and second intruder bearings,

said receiving means including a first channel for processing said sum signal, a second channel for processing said delta signals, and a switch between said array and said second channel for alternately providing said first and second delta signals to said second channel.