Rear-looking apparatus and method for detecting contrails

• US 5,285,256 A
• Filed: 07/28/1992
• Issued: 02/08/1994
• Est. Priority Date: 07/28/1992
• Status: Expired due to Fees

• Current Assignee: Ophir Corporation
• Original Assignee: Ophir Corporation
• Inventors: Nelson, Loren D., MacPherson, David C.
• Primary Examiner(s): Johnston, Jill A.
• Application Number:
  US07/921,502
• Time in Patent Office: 560 Days
• Field of Search: 356/4, 356/5, 356/342, 340/601, 340/945
• US Class Current: 356/342
• CPC Class Codes: G01S 17/04 Systems determining the presence of a target
• CPC Class Codes: G01S 17/88 Lidar systems specially adapted for specific applications

Abstract

Contrail detection aft of an aircraft is provided by a rear-looking ranging system carried by the aircraft. A randomly modulated laser beam is directed into a detection volume aft of the aircraft for scatter back toward a detector on the aircraft. Bistatic mounting of a laser and a telescope of the detector preclude sensing of the scattered beam forward of the detection volume. Processing of the detected scattered beam includes cross correlation and analysis to indicate the formation of the contrail aft of the aircraft.

Claims

1. An airborne system for indicating that a contrail is forming at a distance behind an aircraft, said contrail having an onset which normally occurs within a predetermined contrail onset range behind the aircraft, said system comprising:

means carried by the aircraft for directing a lidar signal behind the aircraft into intersection with at least the onset of a contrail which has formed behind the aircraft, the onset of the contrail being within the contrail onset range, said lidar signal being scattered back toward the aircraft by the contrail to form a return signal having an amplitude related to said distance at which the contrail forms behind the aircraft, said directing means modulating the lidar signal according to a pseudorandom pattern, the return signal having a pattern related to said pseudorandom pattern; and

means carried by the aircraft for cross correlating said pattern of the return signal and the lidar signal to generate a profile of the amplitude of the return signal according to said distance from the aircraft, said profile having a peak within the onset range and corresponding to said distance of the onset behind the aircraft for indicating that the contrail is being formed behind the aircraft.

2. A system according to claim 1, wherein the onset range starts at a selected distance behind the aircraft, further comprising:

said directing means directing said lidar signal along a first path into the contrail onset range;

said cross correlating means being responsive to the return signal scattered along a second path; and

said directing means and said cross correlating means being interrelated such that said first and second paths intersect at a distance behind the aircraft past the selected distance and within the contrail onset range.

3. A system according to claim 2, further comprising:

a platform on said aircraft;

said directing means and said cross correlating means being mounted on said platform offset from each other.

4. A system according to claim 1, further comprising:

said cross correlating means comprising;

means for temporally grouping the return signal;

means for cross correlating the pattern of the lidar signal with the pattern of the temporally grouped return signal to generate an output indicative of the amplitude of the return signal with respect to distance behind the aircraft from which the lidar signal was scattered back toward the aircraft; and

means for indicating that there is a peak in the amplitude corresponding to a distance behind the aircraft, which distance is within the onset range, the peak indicating that a contrail is being formed behind the aircraft.

5. A system for detecting a contrail resulting from operation of an aircraft at high altitude, wherein the contrail forms along an axis at a distance behind the aircraft within a contrail onset range generally close but not immediately behind the aircraft and has an onset within the onset range, said system comprising:

means for generating a continuous-wave output signal having a pseudorandom output sequence;

means for mounting said generating means on said aircraft to direct the output laser signal into intersection with a contrail extending along the axis behind the aircraft, said signal being scattered back toward the aircraft by the contrail onset to form a return signal having an amplitude related to said distance and having a sequence related to the output sequence;

means for temporally grouping the return signal;

means for cross correlating the output sequence with the temporally grouped return signal to generate an output indicative of the amplitude of the return signal with respect to distance relative to the aircraft from which the return signal was scattered back toward the aircraft; and

means for determining whether there is a peak in the amplitude of the return signal corresponding to a first distance from the aircraft which is within the onset range to indicate that a contrail is resulting from operation of the aircraft.

6. A system according to claim 5, wherein the output laser signal has a wavelength and is controlled so as to minimize detection at a second distance away from the aircraft, said second distance being great relative to the contrail onset range, said system further comprising:

means for controlling said generating means so that the wavelength of the output laser signal is selected so that the laser signal is not visible.

7. A system according to claim 6, wherein the output signal having said wavelength is highly absorbed by water vapor.

8. A system according to claim 6, further comprising:

means for moving said mounting means and said grouping means in synchronism to sweep the output signal relative to the axis behind the aircraft and to receive the return signal.

9. A system according to claim 6, further comprising:

means for sensing the lidar signal; and

means responsive to the lidar signal having a wavelength other than the selected wavelength for controlling said generating means to generate said lidar signal at the selected wavelength.

10. A system according to claim 5, further comprising:

said mounting means including a first aperture for permitting said output signal to be directed along a first path; and

means for admitting to said grouping means only that portion of the return signal which is returned along a second path positioned at an angle from said first path so that said portion is received from not less than a minimum distance from the generating means.

11. A system according to claim 5, wherein the aircraft has a plurality of engines the operation of one of which may result in a contrail being formed behind the aircraft without the operation of a second of said engines resulting in the formation of a contrail, said system further comprising:

said system having one of said generating means for each of said engines, each of said generating means being operated at a different output sequence which is distinguishable from the other output sequences;

said output signals being scattered back by each said contrail to form one of said return signals from each of said contrails, said return signals each having a different output sequence; and

said grouping and said cross correlating means being effective separately with respect to each of said different output sequences of said return signals to indicate separately for each particular one of said engines whether a contrail is resulting from the operation of said particular engine.

12. A system according to claim 5, further comprising:

said mounting means being effective in directing said output signal behind the aircraft by moving said output signal in a sweeping path to bring said output signal into intersection with a leading edge of any contrail, said sweeping being relative to the axis so that at least some portion of the leading edge of any contrail which has formed at a location behind the aircraft is in the path of the output signal to produce said return signal from said portion;

movable means for receiving said return signal from said portion of said leading edge of said contrail, said movable means being moved in coordination with said sweeping path of said output signal to identify the location of the portion of the contrail which is causing the return signal at a particular time; and

means for correlating the amplitude of the return signal scattered back from a particular range, with the range of the portion of the leading edge of the contrail which has resulted in that return signal to define a profile indicating the range of the leading edge of the contrail.

13. A system for detecting a contrail which results from operation of an engine of an aircraft, the contrail forming at a distance behind the aircraft and having an onset corresponding to a front portion of the contrail, the onset generally being within a maximum distance from said aircraft, said maximum distance being short relative to the distance at which the contrail extends behind the aircraft, the front portion having a definable shape, said system comprising:

means for generating an output lidar signal;

means for modulating the lidar signal according to a pseudorandom pattern;

means for storing a cross correlation pattern corresponding to the pseudorandom pattern;

means for mounting said generator means on said aircraft to direct said output lidar signal into any contrail which forms within the maximum distance so that said signal is scattered back toward the aircraft and forms a return signal having amplitude and a pattern related to the pseudorandom pattern;

means carried by the aircraft for detecting the return signal and generating a count signal;

means responsive to the count signal for resolving the count signal into temporal bins to form a histogram; and

means for cross correlating said cross correlation pattern with the histogram to define a profile of the amplitude of the return signal as a function of the distance from the aircraft, said profile having a peak at one such distance within the maximum distance to indicate that a contrail has formed as a result of operation of said engine.

14. A system according to claim 13, wherein the contrail onset also generally occurs between said maximum distance and a minimum distance behind the aircraft, the engine having a longitudinal axis extending behind the aircraft, said system further comprising:

said generating means directing the lidar signal behind the engine along a first path at an acute angle relative to the longitudinal axis; and

said resolving means being responsive to the return signal scattered back toward the engine along a second path which intersects the first path between the minimum and maximum distances.

15. A system for indicating that there is a contrail resulting from operation of an engine of an aircraft, said system indicating that the contrail has formed behind the engine in a detection volume having a selected dimension starting at a given distance aft of the engine and extending rearwardly of the engine, the contrail having an onset at which a front portion of the contrail is positioned, the onset generally being within a maximum distance from the aircraft, said maximum distance being short relative to the distance at which the contrail extends behind the engine and long relative to the given distance, the front portion having a definable shape, said system comprising:

means for generating a lidar output signal;

means for modulating the lidar signal according to a pseudorandom pattern;

means for storing a cross correlation pattern corresponding to the pseudorandom pattern;

means for mounting said generating means on the aircraft offset from the engine by a first offset distance and for directing said lidar signal transversely of said selected dimension to intersect any contrail onset which forms within said detection volume so that said lidar signal is scattered back toward the engine and forms a return signal having amplitude and a pattern related to the pseudorandom pattern;

means for tracking the location of said contrail, said tracking means being mounted on the aircraft offset from the engine by a second offset distance, the second distance being different from the first offset distance, said tracking means being responsive to the return signal for resolving the return signal into temporal bins to form a histogram; and

means for cross correlating the cross correlation pattern with the histogram to define a profile of the amplitude of the return signal as a function of distance from the aircraft, the profile having a peak at a distance within the selected dimension of the detection volume to indicate that a contrail has formed as a result of said engine.

16. An indicating system according to claim 15, wherein said engine has a thrust axis extending parallel to said selected dimension, said system further comprising:

said mounting and directing means being offset from the thrust axis of said engine to cause the lidar signal to be scattered back in paths within the detection volume, said detection volume being frustoconical; and

said resolving means including a lidar signal detector carried by said mounting means and moved in synchronism with the return signal.

17. An indicating system according to claim 16, further comprising:

said detector being an avalanche photodiode; and

means for operating said avalanche photodiode below the diode breakdown voltage of said photodiode.

18. An indicating system according to claim 16, wherein said aircraft has first and second ones of said engines, and a first of said indicating systems is provided for said first engine and a second of said indicating systems is provided for said second engine, said first and second indicating systems further comprising:

said modulating means of said first and second systems causing the lidar signals generated by said respective first and second systems to have different pseudorandom patterns having no relative cross correlation.

19. A system according to claim 15, further comprising:

said mounting means moving said detector to receive a lidar signal scattered from within said detection volume and not a lidar signal reflected from a position between said engine and the given distance aft of said engine.

20. A system for indicating according to claim 15, said lidar signal having a wavelength, further comprising:

said generating means causing the wavelength of the lidar signal to be a selected wavelength both in the invisible range and at which the lidar signal is highly absorbed by water vapor to limit the amplitude of the lidar signal transmitted beyond the detection volume aft of said aircraft.

21. A system for indicating according to claim 15, further comprising:

said modulating means causing said pseudorandom pattern to be an A-sequence pseudorandom code; and

said generating means causing said lidar signal to be continuous-wave at power which is low relative to a pulsed signal.

22. A method of determining whether a contrail is forming behind an aircraft, wherein the contrail may be in or adjacent to a cloud, comprising the steps of:

directing a lidar beam rearward of the aircraft;

defining a first zone immediately aft of the aircraft, a second zone immediately aft of the first zone and in which no contrail normally forms, and a third zone immediately aft of the second zone and in which a contrail normally forms;

detecting a return signal backscattered by said contrail if said contrail is forming and by any such cloud in said second zone;

obtaining a cloud signal representing the average value of the return signal returned from the second zone;

obtaining a first contrail signal representing a peak in the value of the return signal returned from a contrail in the third zone;

obtaining a second contrail signal representing the average of the return signal returned from the third zone; and

comparing the cloud signal to the second contrail signal and determining, if the value of the cloud signal is greater than the value of the second contrail signal, that no contrail is forming behind the aircraft.

23. The method of claim 22, comprising the further steps of:

upon determining that the value of the cloud signal does not exceed the value of the second contrail signal, determining whether the second contrail is very large as compared to a threshold to indicate that a contrail is forming behind the aircraft.

24. The method of claim 23, comprising the further steps of:

determining the value of noise which is included in the return signal; and

comparing the noise value to the value of the first contrail signal and, if the latter value is not substantially greater than the former value, determining that no contrail is forming behind the aircraft.

25. The method of claim 24, comprising the further step of:

if the comparing step results in the value of the first contrail signal being substantially greater than the noise value, determining that the first contrail signal is temporally limited to a defined temporal interval to indicate that a contrail is forming behind the aircraft.

26. The method of claim 25 comprising the further steps of:

if no contrail indication results from the comparing and determining steps, then comparing the first contrail signal and the cloud signal to respective thresholds; and

if either the value of the first contrail signal or the value of the cloud signal exceed the respective threshold, generating a warning that the formation of a contrail is imminent.