Pilot warning system

• US 5,506,590 A
• Filed: 06/30/1993
• Issued: 04/09/1996
• Est. Priority Date: 08/13/1990
• Status: Expired due to Fees

• Current Assignee: Jerry B. Minter
• Original Assignee: Jerry B. Minter
• Inventors: Minter, Jerry B.
• Primary Examiner(s): ISSING, GREGORY C
• Application Number:
  US08/085,023
• Time in Patent Office: 1,014 Days
• Field of Search: 342/455, 342/417, 342/462, 342/123, 342/120, 342/432, 364/461
• US Class Current: 342/462
• 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 13/933 of aircraft or spacecraft

Abstract

This invention relates to a system to alert an aircraft pilot of the presence and general location of other aircraft that might constitute a collision threat to the pilot'"'"'s aircraft. A first and second antenna on the upper paid lower surfaces of the aircraft each operate in first and second modes characterized by respective first and second directivity conditions. The first and second antennas directly receive pulse signals from a source in order to determine the relative time of arrivals and thus the relative altitude of the source to the aircraft. Analysis means compares amplitudes of responses in the first and second modes to provide an angle indicating signal without having to generate radio signals other than those already being generated by equipment in the other aircraft in response to ground ATC interrogation.

Claims

1. A system to alert the pilot of an aircraft of a collision threat and of the direction in which to look for that threat, said system comprising:

(a) antenna means to receive, directly from a source, pulse signals that are on a carrier having a certain wavelength λ and

were transmitted from a source located at a certain direction from the antenna means, the antenna means comprising a ground plane and a first element extending from the ground plane by a distance giving the first element an effective length of the first antenna means having first and second modes of operation characterized, respectively, by first and second directivity conditions resulting in a first gain for signals from said certain direction when the antenna means is in the first mode and a second gain for signals from said certain direction when the antenna means is in the second mode;

(b) receiving means comprising an input circuit connected to the antenna means to receive the pulse signals therefrom to produce a first response to the signals received when the antenna means is in the first mode and a second response to the signals received when the antenna is in the second mode; and

(c) first analytical means associated with the receiving means to make a comparison between the first and second responses and to produce an angle-indicating signal based on the comparison;

(d) second antenna means to receive the pulse signals directly from the source, the second antenna means being connected to the receiving means, one of the antenna means being on an upper surface of the aircraft and the other antenna means on a lower surface of the aircraft directly below the one antenna means; and

(e) second analytical means associated with the receiving means to compare the relative times of arrival of the signals at the first and second antenna means to determine the altitude of the source relative to the altitude of the aircraft.

2. The system of claim 1 comprising indicating means connected to the first analytical means to communicate to the pilot the direction to look for the source.

3. The system of claim 2 indicating means are only actuated when the collision threat is within about +5°

of a plane that includes the direction of flight of the aircraft.

4. The system of claim 2 indicating means are only actuated when the ratio of the distance v in feet of the collision threat perpendicular to a plane that includes the direction of flight of the aircraft to the distance d in miles from the aircraft to the collision threat is:

space="preserve" listing-type="equation">v/d<

500.

5. The system of claim 1 in which the second antenna means is omnidirectional.

6. The system of claim 1 in which the aircraft has a vertical axes and the antennas extend parallel to the vertical axis.

7. The system of claim 2 in which the indicating means comprise individual indicators for each of a plurality of directions.

8. The system of claim 2 in which the indicating means comprise lights spaced angularly about a point of origin corresponding to the location of the pilot.

9. The system of claim 8 in which the lights are of different colors according to distance of the source from the aircraft.

10. The system of claim 8 in which the aircraft comprises an instrument panel and the lights are mounted in a circle on the instrument panel.

11. The system of claim 2 in which the indicating means indicating means comprise audible means to indicate the presence of a collision threat.

12. The system of claim 2 in which the pulse signals comprise at least one group of transponder pulse signals comprising first and second framing pulses and encoding pulses between the framing pulses, and the receiving means comprises control means connected to the first antenna means to shift the first antenna means from one of its modes of operation to the other in predetermined relationship to the pulse signals.

13. The system of claim 12 in which the control means comprises means responsive to a leading edge portion of at least one of the pulses to shift the mode of operation of the first antenna means during that pulse.

14. The system of claim 12 in which the pulses are transmitted in pairs of first and second framing pulses, the second framing pulse in each pair having a leading edge at a predetermined time after the leading edge of the first framing pulse of that pair, control means comprising means to shift the mode of operation of the first antenna means before the second framing pulse of a pair of pulses and for at least a substantial part of that second framing pulse.

15. The system of claim 12 in which the control means comprises switching means of controllable conductivity to switch the first antenna means from the first mode of operation to the second mode of operation between first and second parts of a received pulse signal.

16. The system of claim 1 in which the aircraft has a fuselage and the upper surface is the top of the fuselage and the lower surface is the bottom of the fuselage.

17. The system of claim 1 in which the first antenna means comprises a second element extending from the conductive ground plane by a distance giving the second element an effective length of , the second element being parallel to the first element and spaced from it in a predetermined direction by a distance between about and .

18. The system of claim 17 in which the predetermined direction is parallel to the central vertical plane of the aircraft.

19. The system of claim 17 comprising a third element extending from the conductive ground plane by a distance giving the third element an effective length of , the third element being parallel to the first element and spaced from it by a distance between about and and in a second predetermined direction different from the first-named predetermined direction.

20. The system of claim 19 in which the second predetermined direction is perpendicular to the first-named predetermined direction.

21. The system of claim 20 in which the first-named predetermined direction is parallel to the central vertical plane of the aircraft.

22. The system of claim 21 comprising a fourth element extending from the conductive ground plane by a distance giving the fourth element an effective length of , the fourth element being parallel to the first element and spaced from it by a distance between about and and in a direction opposite the first-named predetermined direction.

23. The system of claim 21 comprising a fifth element extending from the conductive ground plane by a distance giving the fifth element an effective length of , the fifth element being parallel to the first element and spaced from it by a distance between about and and in a direction opposite the second predetermined direction.

24. The system of claim 23 in which the distance between the first element and each of the second, third, fourth, and fifth elements is substantially equal to .

25. The system of claim 17 in which the second antenna means comprises:

(a) a second conductive ground plane; and

(b) an antenna element extending from the ground plane by a distance giving the last-named antenna element an effective length of .

26. The system of claim 17 comprising:

(a) a plurality of additional elements, each having a location thereon adjacent the ground plane and extending from the ground plane by a distance giving each of the plurality of elements an effective length of , each of the plurality of elements being parallel to the first element and spaced from it by a distance between about and and in a respective direction, each different from the first-named predetermined direction; and

(b) a corresponding plurality of quarter wave transmission lines, each connected end to end between the ground plane and a respective one of the locations on a respective one of the additional elements and being short-circuited at the ground plane.

27. The system of claim 17 in which the distance between the first element and the second element of the first antenna means is substantially equal to .

28. The system of claim 27 further comprising:

(a) first connecting means connecting the location on a first one of the elements to the input circuit of the receiving means;

(b) second connecting means connecting the location on the other antenna element to the conductive ground plane, said second connecting means comprising means of controllable conductivity; and

(c) switching means comprising driving means connected to the means of controllable conductivity to change the state of conductivity thereof to change the mode of operation of the first antenna means.

29. The system of claim 28 in which the switching means comprises:

(a) means providing a point having a low impedance to the ground plane at the wavelength λ

;

(b) semiconductor means connected between said point and said location on the second element adjacent the ground plane, and

(c) means connected to the semiconductor means and to the receiving means to be controlled by the receiving means to supply a current pulse to the semiconductor means to cause the semiconductor means to be conductive to furnish a low-impedance path effectively short-circuiting the location on the second element to the conductive ground plane in response to reception by the antenna means of a pulse signal having the wavelength λ

.

30. The system of claim 28 comprising first and second transmission lines conductively connecting the locations on the first and second elements, respectively, to the ground plane, each of the transmission lines having an effective length approximately equal to between the respective location and the ground plane and being short-circuited at the ground plane.

31. The system of claim 28 in which the total effective length of the second element of the first antenna means is , and one end of the second element is conductively connected to the conductive ground plane, said location on the second element being at the electrical center thereof, and the portion of the second element and the ground plane comprising a transmission line short-circuited at the ground plane end.

32. The system of claim 28 in which the total effective length of the first element of the first antenna means is , and one end of the first element is conductively connected to the conductive ground plane, said location on the first element being at the electrical center thereof, and the portion of the first element and the ground plane comprising a transmission line short-circuited at the ground plane end.

33. The system of claim 28 in which the second element comprises:

(a) a quarter-wave first part extending from the conductive ground plane; and

(b) a second part comprising a quarter-wave transmission line conductively connected end to end with the first part at said location on the second element and to the conductive ground plane at the end of the transmission line remote from the first part.

34. The system of claim 33 in which the first element comprises:

(a) a quarter-wave first part extending from the conductive ground plane; and

(b) a second part comprising a second quarter-wave transmission line conductively connected end to end with the first part at said location on the first element and to the conductive ground plane at the end of the second transmission line remote from the first part of the first element.

35. The system of claim 34 in which each of the transmission lines is a strip line.

36. The system of claim 28 in which the second connecting means comprises a fast-response diode connected between a point on the second element substantially coplanar with the conductive ground plane and a circuit point having a low impedance to ground at the carrier frequency.

37. The system of claim 36 in which the circuit point having a low impedance to ground at the carrier frequency comprises one end of a quarter-wave transmission line the other end of which has a high impedance to ground.

38. The system of claim 37 in which the means to supply a current to the semiconductor means comprises a high-speed transistor having a collector-emitter circuit connected in series between the diode and a source of operating current.

39. The system of claim 38 comprising an amplifier having an input terminal connected to the junction between the first and second parts of the first element by a conductive link having a length less than the wavelength λ

.

40. The method of determining, in an aircraft that has first and second vertically spaced antenna means, the location of a pulse signal source relative to the aircraft, the first antenna means being characterized by first and second modes of directivity, said method comprising the steps of:

(a) receiving at least a first part of the pulse signal directly from the source by way of the first antenna means and with the first antenna means in the first mode;

(b) receiving at least said first part of the pulse signal directly from the source by way of the second antenna means;

(c) comparing the time of arrival of the first part of the pulse signal by way of the first antenna means with the time of arrival of the same first part of the pulse signal by way of the second antenna means to produce relative altitude information indicating, from the compared times of arrival, whether or not the source is within a predetermined range of altitudes relative to the altitude of the aircraft;

(e) switching the first antenna means from the first mode to the second mode;

(f) receiving a second part of the pulse signal with the first antenna means in the second mode;

(g) comparing a ratio of one of the parts to the other part with a table of entries of such ratios, each entry being correlated with a direction; and

(h) generating a direction-indicating signal according to the entry that corresponds to the ratio of one of the first and second parts to the other of the first and second parts.

42. The method of claim 40 in which the step of generating the indicating signal comprises the step of comparing the amplitude of the second part of the pulse signals with the amplitude of the first part.

43. The method of claim 42 in which the step of comparing the amplitude of the first and second signals comprises forming a ratio of the amplitude of one of the signals to the amplitude of the other signal, said method further comprising the step of comparing the ratio with a table of such ratios correlated with the direction of maximum gain of the antenna means.

44. The method of claim 42 in which the signal is a transponder signal comprising a pair of framing pulses and the first part is one of the framing pulses and the second part is the other of the pair of framing pulses.

45. The method of claim 42 in which the signal is a transponder signal comprising a pair of framing pulses and the first part is the first part of one of the framing pulses and the second part is a later part of the same framing pulse.

46. The method of claim 40 comprising the step of generating the pulse signals in the aircraft and receiving said signals reflected from stationary reflecting means extending into the path of the aircraft.

47. The method of claim 40 in which the pulse signal is a transponder signal and includes identification information encoded therein identifying the source, said method comprising the further steps of:

(a) storing the identification information in association with the relative altitude information from the same transponder signal;

(b) repeating the comparison of subsequently received pulse signals; and

(c) comparing information from the subsequently received pulse signals with previously stored information of the same kind to determine any change in the relative location of the source of transponder signals.

48. The method of claim 47 comprising the steps of:

(a) measuring the field strength of the transponder signal;

(b) storing information of the measured field strength; and

(c) comparing the stored field strength information with the field strength of subsequently received ones of the transponder signals.

49. The method of claim 40 in which the step of generating an indicating signal comprises the steps of:

(a) generating a first locally generated pulse signal at a predetermined time after the beginning of the first part of the received pulse signals;

(b) changing the directivity of the antenna means from the omnidirectional mode to the directional mode in response to the generated pulse signal; and

(c) determining whether a second pulse signal is locally generated in response to the change of directivity of the antenna.

41. The method of claim '"'"'in which the first mode is omnidirectional and the second mode is directional.

50. In a system to alert a pilot flying in a first aircraft to the presence of a second aircraft when radio signals in response to radar interrogation are being transmitted from the second aircraft on a standard response frequency and in the form of at least first and second pulses, each having a standard waveform and a predetermined time between leading edges of each of the pulses, the invention comprising:

(a) antenna means on the first aircraft, said antenna means comprising;

(i) a conductive ground plane,

(ii) a parasitic antenna element having an effective length of about at the standard frequency and extending perpendicularly to the ground plane and having a location on it coplanar with the ground plane,

(iii) a plurality n of antenna elements, each having an effective length of about at the standard frequency and being angularly spaced apart around the parasitic element and being located at a distance of about to about from the parasitic element;

(b) receiving circuit means comprising n input sections, each connected to a respective one of the antenna elements and tuned to receive the signals from the second aircraft;

(c) controllable short-circuiting means connected in series between the ground plane and said one end of the parasitic element to short-circuit said one end to the ground plane when the short-circuit means is actuated; and

(d) control means connecting the receiving circuit means to the controllable short-circuiting means to actuate the short-circuiting means at a predetermined time after the start of one of the pulses.

51. The system of claim 50 in which n=4.

52. The system of claim 51 in which the antenna elements are angularly spaced 90°

apart.

53. The system of claim 50 in which the control means is timed to actuate the short-circuiting means at said predetermined time after the leading edge of the first pulse.

54. In a system to alert a pilot flying in a first aircraft to the presence of a second aircraft when radio signals in response to radar interrogation are being transmitted from the second aircraft on a standard response frequency and in the form of at least first and second pulses, each having a standard waveform and a predetermined time between the leading edges of the pulses, the invention comprising:

(a) antenna means on the first aircraft, said antenna means comprising;

(i) a conductive ground plane,

(ii) a parasitic antenna element having an effective length of at the standard frequency and extending perpendicularly to the ground plane and having one end of the effective length substantially coplanar with the ground plane,

(iii) four antenna elements, each having a length of at the standard frequency and being spaced 90°

apart around the parasitic element and being located at a distance of from the parasitic element;

(b) receiving circuit means comprising four input sections and an output section, each of the input sections being connected to a respective one of the antenna elements and tuned to receive the signals received by that element;

(c) controllable short-circuiting means connected to the output section to be actuated by a signal therefrom in response to the radio signals transmitted from the second aircraft and received by any of the antenna elements, the short-circuiting means being connected in series between the ground plane and said one end of the effective length of the parasitic element to short-circuit said one end to the ground plane when the short-circuit means is actuated; and

(d) means connecting the output section of the receiving circuit means to the controllable short-circuiting means to actuate the short-circuiting means at a predetermined time after the start of one of the pulses.