Onboard aircraft flight path optimization system

• US 5,615,118 A
• Filed: 12/11/1995
• Issued: 03/25/1997
• Est. Priority Date: 12/11/1995
• Status: Expired due to Term

• Current Assignee: Robert K. Frank
• Original Assignee: Robert K. Frank
• Inventors: Frank, Robert K.
• Primary Examiner(s): ZANELLI, MICHAEL J
• Application Number:
  US08/570,598
• Time in Patent Office: 470 Days
• Field of Search: 364/424.06, 364/442, 364/420, 364/444, 364/453, 364/557, 364/433, 340/968, 73/170.02, 342/26, 250/338.1, 250/338.5
• US Class Current: 701/4
• CPC Class Codes: G01C 21/183 Compensation of inertial measurements, e.g. for temperature effects
• CPC Class Codes: G01S 13/86 Combinations of radar systems with non-radar systems, e.g. sonar, direction finder
• CPC Class Codes: G01S 13/953 mounted on aircraft
• CPC Class Codes: G01S 7/22 Producing cursor lines and indicia by electronic means
• CPC Class Codes: G05D 1/0005 with arrangements to save energy
• CPC Class Codes: Y02A 90/10 Information and communication technologies [ICT] supporting adaptation to climate change, e.g. for weather forecasting or climate simulation

Abstract

An onboard aircraft flight optimization system that includes an onboard performance management computer, a control display unit, an infrared probe, a temperature probe, a weather radar, an inertial navigation system, and comparing apparatus. The control display unit inputs a position remote from an aircraft into the performance management computer. The infrared probe determines temperature at the position remote from the aircraft and generates a remote temperature signal received by the performance management computer. The temperature probe determines temperature at the aircraft and generates a local temperature signal received by the performance management computer. The weather radar determines wind at the position remote from the aircraft and generates a remote wind signal received by the performance management computer. The inertial navigation system determines wind at the aircraft and generates a local wind signal received by the performance management computer. And, the comparing apparatus is disposed in the performance management computer and compares the remote wind signal with the local wind signal and compares the remote temperature signal with the local temperature signal so as to determine the position remote from the aircraft where the remote wind signal is less than the local wind signal so that an altitude can be achieved that has less head wind and is therefore more economically efficient.

Claims

1. An onboard aircraft flight optimization system, comprising:

a) an onboard performance management computer;

b) an onboard control display unit for inputting a position remote from an aircraft into said onboard performance management computer;

c) an onboard infrared probe for determining temperature at the position remote from the aircraft and generating a remote temperature signal received by said onboard performance management computer;

d) an onboard temperature probe for determining temperature at the aircraft and generating a local temperature signal received by said onboard performance management computer;

e) an onboard weather radar for determining wind at the position remote from the aircraft and generating a remote wind signal received by said onboard performance management computer;

f) an onboard inertial navigation system for determining wind at the aircraft and generating a local wind signal received by said onboard performance management computer; and

g) onboard comparing means disposed in said onboard performance management computer for comparing said remote wind signal with said local wind signal and comparing said remote temperature signal with said local temperature signal so as to determine the position remote from the aircraft where said remote wind signal is less than said local wind signal so that an altitude can be achieved that has less head wind and is therefore more economically efficient.

2. The system as defined in claim 1, wherein said onboard control display unit includes an onboard pilot keyboard for inputting the position remote from the aircraft.

3. The system as defined in claim 2, wherein said onboard weather radar is a dual radar system that includes backup protection against a single system failure.

4. The system as defined in claim 3, wherein said onboard weather radar is a doppler weather surveillance radar system designed to provide early weather detection of wind shear and turbulence.

5. The system as defined in claim 4, wherein said onboard weather radar calculates both the speed and direction of the wind at the position remote from the aircraft.

6. The system as defined in claim 5, wherein said onboard weather radar detects the speed and the direction of the wind at the position remote from the aircraft up to a range of 300 nm.

7. The system as defined in claim 6, wherein said onboard weather radar detects the speed and the direction of the wind at the position remote from the aircraft over a scan angle of at least 170 degrees.

8. The system as defined in claim 7, wherein said onboard weather radar provides terrain display to detect rough terrain turbulence.

9. The system as defined in claim 8, wherein said onboard weather radar includes a pencil antenna beam for terrain display at altitudes above 25,000 feet and an elongated antenna beam for terrain display at altitudes below 25,000 feet.

10. The system as defined in claim 9, wherein said onboard comparing means compares said remote wind signal with said local wind signal and compares said remote temperature signal with said local temperature signal at intervals of 50 nautical miles.

11. The system as defined in claim 10, wherein said onboard weather radar detects clear air turbulence.

12. The system as defined in claim 11, wherein said onboard weather radar detects clear air turbulence by receiving scattering from conglomerates of small targets concentrated at specific locations in the atmosphere in a range corresponding to the top of the planetary boundary layer.

13. The system as defined in claim 12, wherein said scattering is visualized as a reflection provided by a mismatch in the atmosphere caused by a change in refractive index of the atmosphere and whose fluctuations are a direct measure of the air motion.

14. The system as defined in claim 13;

further comprising an onboard clear air turbulence alert computer.

15. The system as defined in claim 14, wherein said onboard clear air turbulence alert computer receives a clear air turbulence signal generated by said onboard weather radar when said onboard weather radar detects clear air turbulence and generates a clear air turbulence alert signal.

16. The system as defined in claim 15;

further comprising an onboard clear air turbulence computer alert.

17. The system as defined in claim 16, wherein said onboard clear air turbulence computer alert illuminates when said onboard clear air turbulence computer alert receives said clear air turbulence alert signal.

18. The system as defined in claim 17, wherein said onboard performance management system computer stores all performance data and engines tables for the aircraft.

19. The system as defined in claim 18, wherein said onboard performance management system computer is coupled to the autopilot, the flight director, and the autothrottle of the aircraft for making automatic corrections in flight path.

20. The system as defined in claim 19, wherein said onboard performance management system computer is in a normal autopilot altitude hold and the autothrottle controls speed according to a cruise option used when engaged in a cruise mode.

21. The system as defined in claim 20, wherein said onboard performance management system computer biases the normal autopilot altitude hold to permit an altitude drift of plus or minus 120 feet to minimize throttle hunt.

22. The system as defined in claim 21, wherein said onboard control display unit further includes an onboard pilot readout.

23. The system as defined in claim 22, wherein said onboard pilot readout is an electronic CRT that displays a first line of alphanumeric text, a second line of alphanumeric text, and a third line of alphanumeric text which together comprise three lines of selected information which can be selectively changed.

24. The system as defined in claim 23, wherein said onboard control display unit further includes a first onboard display line switch to select said first line of alphanumeric text for data entry and text change.

25. The system as defined in claim 24, wherein said onboard control display unit further includes a second onboard display line switch to select said second line of alphanumeric text for data entry and text change.

26. The system as defined in claim 25, wherein said onboard control display unit further includes a third onboard display line switch to select said third line of alphanumeric text for data entry and text change.

27. The system as defined in claim 26, wherein said onboard pilot keyboard consists of 10 keys and permits data insertion onto a selected one of said first line of alphanumeric text, said second line of alphanumeric text, and said third line of alphanumeric text.

28. The system as defined in claim 27, wherein said onboard control display unit further includes an onboard insert key.

29. The system as defined in claim 28, wherein said onboard insert key is pressed to enter said first line of alphanumeric text, said second line of alphanumeric text, and said third line of alphanumeric text.

30. The system as defined in claim 29, wherein said onboard insert key illuminates when pressed and is extinguished when said first line of alphanumeric text, said second line of alphanumeric text, and said third line of alphanumeric text are entered into said onboard performance management system computer.

31. The system as defined in claim 30, wherein said onboard control display unit further includes an onboard climb light, an onboard cruise light, and an onboard descent light to indicate flight mode of said onboard performance management system computer.

32. The system as defined in claim 31, wherein said onboard control display unit further includes an onboard climb key to display climb data and permit insertion of climb commands.

33. The system as defined in claim 32, wherein said onboard control display unit further includes an onboard cruise key to display cruise data and permit insertion of cruise speed commands.

34. The system as defined in claim 33, wherein said onboard control display unit further includes an onboard descent key to display descent data and permit insertion of decent rates and speeds.

35. The system as defined in claim 34, wherein said onboard control display unit further includes an onboard planning key to display planning data and permit configuration selection, preflight data insertion and step climb data.

36. The system as defined in claim 35, wherein said onboard control display unit further includes an onboard status light that indicates performance management system computer malfunction.

37. The system as defined in claim 36, wherein said onboard control display unit further includes an onboard clear key to clear erroneous data if the onboard insert key has not been pressed.

38. The system as defined in claim 37, wherein said onboard control display unit further includes an onboard forward back slew switch to cycle additional data onto said onboard pilot readout.

39. The system as defined in claim 38, wherein said onboard control display unit further includes an onboard test switch to produce uniform squares on said onboard pilot readout.

40. The system as defined in claim 39, wherein said onboard inertial navigation system when activated by said onboard pilot keyboard, produces an aiming signal for aiming said onboard weather radar and said onboard infrared probe.

41. A method of using an onboard aircraft flight optimization system, comprising the steps of:

a) pressing manually a first onboard display line switch of an onboard control display unit of said onboard aircraft flight optimization system;

b) entering manually, via an onboard pilot keyboard of said onboard control display unit, a selected N, S, E, or W coordinates of a remote position for which routing analysis is desired into an onboard performance management system computer of said onboard aircraft flight optimization system;

c) appearing automatically said selected N, S, E, or W coordinates of said remote position as a first line of alphanumeric text on an onboard pilot readout of said onboard control display unit;

d) pressing manually a second onboard display line switch of said onboard control display unit;

e) entering manually, via said onboard pilot keyboard, a selected flight level altitude of said remote position for which routing analysis is desired into said onboard performance management system computer;

f) appearing automatically said selected flight level altitude of said remote position as a second line of alphanumeric text on said onboard pilot readout;

g) instructing automatically, via said onboard performance management system computer, an onboard inertial navigation system of said onboard aircraft flight optimization system to produce an aiming signal;

h) receiving automatically said aiming signal by a weather radar of said onboard aircraft flight optimization system and an onboard infrared probe of said onboard aircraft flight optimization system;

i) aiming automatically said onboard weather radar and said onboard infrared probe towards said remote position for which routing analysis is desired;

j) determining automatically a remote wind measurement at said remote position by said onboard weather radar and said onboard inertial navigation system;

k) sending automatically said remote wind measurement to said onboard performance management system computer;

l) determining automatically a remote temperature measurement at said remote position by an onboard infrared probe of said onboard aircraft flight optimization system;

m) sending automatically said remote temperature measurement to said onboard performance management system computer;

n) displaying automatically said remote wind measurement and said remote temperature measurement as a third line of alphanumeric text of said onboard pilot readout;

o) determining a local temperature measurement by an onboard temperature probe of said onboard aircraft flight optimization system;

p) sending automatically said local temperature measurement to said onboard performance management system computer;

q) determining a local wind measurement by said onboard inertial navigation system;

r) sending automatically said local wind measurement to said onboard performance management system computer;

s) comparing automatically, by said onboard management system computer, said remote wind measurement with said local wind measurement which are automatically updated every 50 nautical miles to seek and determine a most efficient cruise level having least head wind and turbulence;

t) comparing automatically, by said onboard performance management system computer, said remote temperature measurement with said local temperature measurement which are automatically updated every 50 nautical miles; and

u) determining automatically a most efficient cruise level within bounds of fuel freeze point.

42. The method as defined in claim 41;

further comprising the step of feeding automatically said most efficient cruise level, by said onboard performance management system computer, to an onboard autopilot of said onboard aircraft flight optimization system and an autothrottle of said onboard aircraft flight optimization system for automatic execution.

43. The method as defined in claim 42;

further comprising the step of displaying said most efficient cruise level for inspection.

44. The method as defined in claim 43;

further comprising the step of programming an onboard clear air turbulence computer of said onboard aircraft flight optimization system to automatically determine when said onboard weather radar detects an atmospheric refraction rate indicative of clear air turbulence and to also automatically determine when the remote temperature measurement is different than that of the jet stream which is also indicative of clear air turbulence.

45. The method as defined in claim 44;

further comprising the step of illuminating an onboard clear air turbulence computer alert by said onboard clear air turbulence computer.