Antenna arrangement and aircraft collision avoidance system

• US 5,552,788 A
• Filed: 06/30/1995
• Issued: 09/03/1996
• Est. Priority Date: 06/30/1995
• Status: Expired due to Fees

• Current Assignee: Ryan International Corp. (Avidyne Corporation)
• Original Assignee: Ryan International Corp. (Avidyne Corporation)
• Inventors: Ryan, Dean E., Ryan, Paul A.
• Primary Examiner(s): Eldred, J. Woodrow
• Application Number:
  US08/497,714
• Time in Patent Office: 431 Days
• Field of Search: 342/30, 342/455, 342/360, 342/362
• US Class Current: 342/30
• CPC Class Codes: G01S 13/762 with special measures concerning the radiation pattern, e.g. S.L.S. aerials or aerial systems providing at least two radiation patterns, e.g. providing sum and difference patterns, H01Q25/00
• CPC Class Codes: G01S 13/767 Responders; Transponders teaching or practice apparatus for gun-aiming or gun-laying using reflecting targets or active targets F41G3/26
• CPC Class Codes: G01S 3/30 derived directly from separate directional systems
• CPC Class Codes: G01S 3/32 derived from different combinations of signals from separate antennas, e.g. comparing sum with difference

Abstract

An antenna arrangement on a host aircraft for generating power signals related to a direction from which a transponder reply signal is received from a threat aircraft. The arrangement includes first and second monopole antenna elements arranged along a first axis of the host aircraft, third and fourth monopole antenna elements arranged along a second axis of the host aircraft, with the second axis being orthogonal to the first axis, a first quadrature combiner coupled to the first and second monopole antenna elements for generating first and second signals from the received reply signal, and a second quadrature combiner coupled to the third and fourth monopole antenna elements for generating third and fourth signals from the received reply signal. The respective power levels of the first, second, third and fourth signals are related to the direction from which the reply signal is received from the threat aircraft.

Claims

1. An antenna arrangement on a host aircraft for generating signals related to a direction from which a transponder reply signal is received from a threat aircraft, the arrangement comprising:

a first monopole antenna element and a second monopole antenna element arranged along a first axis of the host aircraft for receiving the reply signal;

a third monopole antenna element and a fourth monopole antenna element arranged along a second axis of the host aircraft for receiving the reply signal, the second axis being orthogonal to the first axis;

a first quadrature combiner coupled to the first and second monopole antenna elements for generating first and second signals from the received reply signal, respective power levels of the first and second signals being related to the direction from which the reply signal is received from the threat aircraft; and

a second quadrature combiner coupled to the third and fourth monopole antenna elements for generating third and fourth signals from the received reply signal, respective power levels of the third and fourth power signals being related to the direction from which the reply signal is received from the threat aircraft.

2. The antenna arrangement according to claim 1, wherein the first axis is a longitudinal axis of the host aircraft and the second axis is a lateral axis of the host aircraft.

3. The antenna arrangement according to claim 2, wherein the first and second monopole antenna elements are located on a first surface of the host aircraft, and third and fourth monopole antenna elements are located on a second surface of the host aircraft.

4. The antenna arrangement according to claim 3, wherein the first surface is a top surface of the host aircraft and the second surface is a bottom surface of the host aircraft.

5. The antenna arrangement according to claim 3, wherein the first surface is a bottom surface of the host aircraft and the second surface is a top surface of the host aircraft.

6. The antenna arrangement according to claim 1, wherein the first axis is oriented 45°

from a longitudinal axis of the host aircraft.

7. The antenna arrangement according to claim 1, wherein the first and second quadrature combiners are each a quadrature hybrid circuit.

8. The antenna arrangement according to claim 7, further comprising a receiver system coupled to the first and second quadrature combiners for generating a bearing information signal from the first, second, third and fourth signals, the bearing information signal related to the direction from which the transponder reply signal is received from the threat aircraft.

9. The antenna arrangement according to claim 8, further comprising a transmitter system coupled to the first and second quadrature combiners for transmitting a transponder interrogation signal from the first, second, third and fourth monopole antenna elements.

10. The antenna arrangement according to claim 9, wherein the transponder interrogation signal is transmitted directionally from the first, second, third and fourth monopole antenna elements.

11. The antenna arrangement according to claim 7, wherein at least one of the first and second monopole antenna elements and the first quadrature combiner, and the third and fourth monopole antenna elements and the second quadrature combiner are a single unit.

12. An aircraft collision avoidance system on a host aircraft, the system comprising:

a first monopole antenna element and a second monopole antenna element arranged along a first axis of the host aircraft for receiving a transponder reply signal from a threat aircraft;

a third monopole antenna element and a fourth monopole antenna element arranged along a second axis of the host aircraft for receiving the reply signal, the second axis being orthogonal to the first axis;

a first quadrature combiner coupled to the first and second monopole antenna elements for generating first and second signals from the received reply signal, respective power levels of the first and second power signals being related to a direction from which the reply signal is received from the threat aircraft;

a second quadrature combiner coupled to the third and fourth monopole antenna elements for generating third and fourth signals from the received reply signal, respective power levels of the third and fourth power signals being related to the direction from which the reply signal is received from the threat aircraft; and

a receiver coupled to the first and second quadrature combiners for generating first, second, third and fourth video signals from the first, second, third, and fourth signals, respectively, the first, second, third and fourth video signals each having an amplitude related to the direction from the host aircraft to the threat aircraft from which the reply signal is received.

13. The aircraft collision avoidance system according to claim 12, wherein the first axis is oriented 45°

from a longitudinal axis of the host aircraft.

14. The aircraft collision avoidance system according to claim 12, wherein the first axis is a longitudinal axis of the host aircraft and the second axis is a lateral axis of the host aircraft.

15. The aircraft collision avoidance system according to claim 14 wherein the first and second monopole antenna elements are located on a first surface of the host aircraft, and the third and fourth monopole antenna elements are located on a second surface of the host aircraft.

16. The aircraft collision avoidance system according to claim 15, wherein the first surface is a top surface of the host aircraft and the second surface is a bottom surface of the host aircraft.

17. The aircraft collision avoidance system according to claim 15, wherein the first surface is a bottom surface of the host aircraft and the second surface is top surface of the host aircraft.

18. The aircraft collision avoidance system according to claim 15, wherein the first and second quadrature combiners are each a quadrature hybrid circuit.

19. The aircraft collision avoidance system according to claim 18, further comprising:

a first comparator responsive to the first and second video signals generating a first comparison signal;

a second comparator responsive to the third and fourth video signals generating a second comparison signal;

a first difference circuit responsive to the first and second video signals generating a first difference signal;

a second difference circuit responsive to the third and fourth video signals generating a second difference signal;

a memory loaded with data representing a table of bearing angles as a function of a pair of comparison signals and magnitudes of a pair of difference signals; and

means for coupling the first and second comparison signals and the first and second difference signals to the memory.

20. The aircraft collision avoidance system according to claim 18, further comprising:

a first analog-to-digital converter responsive to the first video signal and producing a first digital signal, the first digital signal representing an amplitude of the first video signal;

a second analog-to-digital converter responsive to the second video signal and producing a second digital signal, the second digital signal representing an amplitude of the second video signal;

a third analog-to-digital converter responsive to the third video and producing a third digital signal, the third digital signal representing an amplitude of the third video signal;

a fourth analog-to-digital converter responsive to the fourth video signal and producing a fourth digital signal, the fourth digital signal representing an amplitude of the fourth video signal; and

a processor for generating a bearing signal from the first, second, third and fourth digital signals, the bearing signal being related to the direction from which the reply signal is received from the threat aircraft.

21. The system according to claim 20, wherein the processor comprises:

a first comparator producing a one bit first polarity signal responsive to the first and second digital signals;

a second comparator producing a one bit second polarity signal responsive to the third and fourth digital signals;

a first digital difference circuit responsive to the first and second digital signals generating a first difference signal;

a second digital difference circuit responsive to the third and fourth digital signals generating a second difference signal;

a memory loaded with data representing a table of bearing angles as a function of a pair of polarity bits and a pair of difference signals; and

means for coupling the first and second difference signals and the first and second polarity signals to the memory.

22. The aircraft collision avoidance system according to claim 12, further comprising a transmitter coupled to the first and second quadrature combiners for transmitting a transponder interrogation signal from the first, second, third and fourth monopole antenna elements.

23. The aircraft collision avoidance system according to claim 22, wherein the transponder interrogation signal is transmitted directionally from the first, second, third and fourth monopole antenna elements.

24. The aircraft collision avoidance system according to claim 12, wherein at least one of the first and second monopole antenna elements and the first quadrature combiner, and the third and fourth monopole antenna elements and the second quadrature combiner are a single unit.

25. A method for determining a bearing of a transponder reply signal received from a threat aircraft with respect to a heading of a host aircraft, the host aircraft including a first monopole antenna element and a second monopole antenna element arranged along a first axis of the host aircraft, a third monopole antenna element and a fourth monopole antenna element arranged along a second axis of the host aircraft, the second axis being orthogonal to the first axis, the method comprising the steps of:

receiving the reply signal at the first, second, third and fourth monopole antenna elements;

generating first, second, third and fourth received signals, the first, second, third and fourth received signals related to the reply signal received at the first, second, third and fourth monopole antenna elements, respectively;

generating first and second signals from a quadrature summation of the first and second received signals, the first signal corresponding to an antenna pattern in a first direction along the first axis of the host aircraft, and the second signal corresponding to an antenna pattern in a second direction along the first axis of the host aircraft;

generating third and fourth signals from a quadrature summation of the third and fourth received signals, the third signal corresponding to an antenna pattern of a first direction along the second axis of the host aircraft, and the fourth power level signal corresponding to an antenna pattern of a second direction along the second axis of the host aircraft;

generating first, second, third and fourth video signals from the first, second, third and fourth signals, respectively, the first, second, third and fourth video signals each having an amplitude related to a bearing of the reply signal received from the threat aircraft with respect to the heading of a host aircraft.

26. The method according to claim 25, wherein the first axis is oriented 45°

from a longitudinal axis of the host aircraft.

27. The method according to claim 25, wherein the first axis is a longitudinal axis of the host aircraft, the first direction along the first axis is in a forward direction of the host aircraft, and the second direction along the first axis is in an aft direction of the host aircraft, and the second axis is lateral axis of the host aircraft, the first direction along the second axis is in a right direction of the host aircraft and the second direction along the second axis is in a left direction of the host aircraft.

28. The method according to claim 25 further comprising the steps of:

comparing the first and second video signals for generating a first polarity signal;

comparing the third and fourth video signals for generating a second polarity signal;

generating first difference signal based on a difference between the first and second video signals;

generating second difference signal based on a difference between the third and fourth video signal; and

generating a bearing signal based on the first and second polarity signals and the first and second difference signals, the bearing signal related to a bearing of the reply signal received from the threat aircraft with respect to a heading of the host aircraft.

29. The method according to claim 25, further comprising the steps of:

converting the first, second, third and fourth video signals to first, second, third and fourth digital signals, respectively, the first, second, third and fourth digital signals each representing an amplitude of the first, second, third and fourth video signals, respectively;

comparing the first and second digital signals for generating a first polarity bit;

comparing the third and fourth digital signals for generating a second polarity bit;

generating a first difference signal based on a difference between the first and second digital signals;

generating a second difference signal based on a difference between the third and fourth digital signals; and

generating a bearing signal based on the first and second polarity bits and the first and second difference signals, the bearing signal related to a bearing of the reply signal received from the threat aircraft with respect to the heading of the host aircraft.

30. The method according to claim 29, wherein the step of generating the bearing signal comprises the step of addressing bearing data stored in a look-up table in a memory.

31. The method according to claim 25, wherein the first and second monopole antenna elements are located on a top surface of the host aircraft.

32. The method according to claim 31, wherein the third and fourth monopole antenna elements are located on a bottom surface of the host aircraft.

33. The method according to claim 25, further comprising the steps of:

generating a transponder interrogation signal; and

coupling the transponder interrogation signal to the first, second, third and fourth monopole antenna elements for transmitting the transponder interrogation signal.

34. The method according to claim 33, wherein the step of coupling the transponder interrogation signal to the first, second, third and fourth monopole antenna elements generates a directionally transmitted signal.