Deflare pitch command

• US 9,546,003 B2
• Filed: 03/14/2014
• Issued: 01/17/2017
• Est. Priority Date: 03/14/2014
• Status: Active Grant

• Current Assignee: Safe Flight Instrument LLC
• Original Assignee: Safe Flight Instrument Corporation
• Inventors: Greene, Randall A., Beyer, Shawn P.
• Primary Examiner(s): Black, Thomas G
• Assistant Examiner(s): LEWANDROSKI, SARA J
• Application Number:
  US14/213,967
• Publication Number:
  US 20160159494A1
• Time in Patent Office: 1,040 Days
• Field of Search: 701/3, 701/4, 701/5, 701/6, 701/7, 701/8, 701/9, 701/10, 701/14, 701/16
• US Class Current: 1/1
• CPC Class Codes: B64C 13/00 Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
• CPC Class Codes: B64C 17/00 Aircraft stabilisation not otherwise provided for
• CPC Class Codes: B64C 19/00 Aircraft control not otherwise provided for
• CPC Class Codes: B64D 2045/008 Devices for detecting or indicating hard landing
• CPC Class Codes: B64D 43/00 Arrangements or adaptations of instruments arrangements of cameras B64D47/08; aeronautical measuring instruments per se G01C
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: B64D 45/04 Landing aids; Safety measures to prevent collision with earth's surface
• CPC Class Codes: B64D 45/08 optical
• CPC Class Codes: G02B 27/01 Head-up displays
• CPC Class Codes: G05D 1/0676 specially adapted for landing
• CPC Class Codes: G05D 1/0808 specially adapted for aircraft
• CPC Class Codes: G05D 1/0816 to ensure stability
• CPC Class Codes: G08G 5/0021 located in the aircraft
• CPC Class Codes: G08G 5/0047 Navigation or guidance aids for a single aircraft details of equipment G08G5/0017
• CPC Class Codes: G08G 5/02 Automatic approach or landing aids, i.e. systems in which flight data of incoming planes are processed to provide landing data landing aids fitted in or to aircraft B64D45/04; visual or acoustic landing aids B64F1/18
• CPC Class Codes: G08G 5/025 Navigation or guidance aids radar or analogous systems specially adapted for landing purposes G01S13/913

Abstract

A pitch command display method includes identifying touchdown of an aircraft, identifying a first value representing an actual pitch reduction rate of the aircraft, identifying a second value representing a target pitch reduction rate of the aircraft, determining a difference between the first value and the second value, and displaying a pitch command when the difference between the first value and second value is greater than a threshold amount and the aircraft has touched down.

Claims

1. A pitch command display method comprising:

identifying an aircraft touchdown comprising determining that landing gear of an aircraft has touched a runway,

identifying a first value representing an actual aircraft pitch reduction rate,

identifying a second value representing a target aircraft pitch reduction rate,

determining a difference between the first value and the second value, and

displaying a pitch command when an aircraft touchdown is identified and the difference between the first value and second value is greater than a threshold amount.

2. The method of claim 1, wherein displaying the pitch command comprises displaying the pitch command on a heads-up display or a primary flight display.

3. The method of claim 1 comprising identifying an elapsed time since aircraft touchdown, wherein displaying the pitch command comprises displaying the pitch command when the elapsed time is identified.

4. The method of claim 1, wherein the target aircraft pitch reduction rate is 1 degree per second.

5. The method of claim 1, wherein the pitch command is a nose-down pitch command.

6. The method of claim 1 comprising

identifying nose gear contact with the runway and

discontinuing display of the pitch command when nose gear contact is identified.

7. The method of claim 6 wherein the second value changes after aircraft touchdown is identified and before nose-gear contact with the runway is identified.

8. The method of claim 1 comprising

identifying an aircraft bounce,

determining a bounce severity,

displaying a bounce recovery instruction based on the bounce severity, the bounce recovery instruction indicating that aircraft pitch should be maintained or that aircraft pitch should be altered,

identifying a bounce recovery, and

discontinuing display of the bounce recovery instruction.

9. The method of claim 8, wherein identifying an aircraft bounce comprises at least one of:

detecting an increase in aircraft acceleration, detecting an upward aircraft speed, detecting an increase in aircraft altitude, and detecting a loss of contact between an aircraft landing gear and a runway.

10. The method of claim 8, wherein determining a bounce severity comprises determining at least one of:

an aircraft acceleration in excess of an acceleration threshold, an upward aircraft speed in excess of a speed threshold, and an increase in aircraft altitude in excess of an altitude threshold.

11. The method of claim 8, wherein identifying a bounce recovery comprises one of detecting a go-around maneuver and detecting contact between an aircraft landing gear and a runway.

12. The method of claim 8 comprising displaying a pitch command after identifying a bounce recovery.

13. The method of claim 8, wherein displaying the bounce recovery instruction comprises displaying a go-around instruction.

14. The method of claim 1, wherein identifying the second value is based on at least one of aircraft flap position, aircraft slat position, and aircraft spoiler position.

15. A pitch command display system comprising:

a first module that identifies an aircraft touchdown, wherein identifying an aircraft touchdown comprises determining that landing gear of an aircraft has touched a runway,

a second module that identifies an actual aircraft pitch reduction rate,

a third module that identities a target aircraft pitch reduction rate,

a pitch command module that determines a difference between the actual aircraft pitch reduction rate and the target aircraft pitch reduction rate, and that provides a pitch command when an aircraft touchdown is identified and the difference between the actual aircraft pitch reduction rate and the target aircraft pitch reduction rate is greater than a threshold amount, and

a display that displays the pitch command.

16. The system of claim 15, wherein the third module identifies the target aircraft pitch reduction rate based on at least one of an aircraft flap position, an aircraft slat position, and an aircraft spoiler position.

17. The system of claim 15, wherein the display comprises a heads-up display or a primary flight display.

18. The system of claim 15 comprising a tenth module that identifies an elapsed time since aircraft touchdown, and wherein the display displays the pitch command after the tenth module identifies the elapsed time.

19. The system of claim 15, wherein the target aircraft pitch reduction rate is 1 degree per second.

20. The system of claim 15, wherein the pitch command is a nose-down pitch command.

21. The system of claim 15 comprising a fourth module that identifies when the nose gear has made contact with the runway and wherein the pitch command module discontinues providing the pitch command when the nose gear has made contact with the runway.

22. The system of claim 21, wherein the third module identifies at least two target aircraft pitch reduction rates after the first module identifies an aircraft touchdown and before the fourth module identifies the nose-gear has made contact with the runway.

23. The system of claim 15 comprising

a fifth module that identifies an aircraft bounce,

a sixth module that determines a bounce severity,

a seventh module that determines a bounce recovery instruction based on the bounce severity, the bounce recovery instruction indicating that aircraft pitch should be maintained or that aircraft pitch should be altered, and

an eighth module that identifies a bounce recovery, wherein the display displays the instruction and discontinues display of the instruction when the eighth module identifies a bounce recovery.

24. The system of claim 23, wherein the fifth module detects at least one of:

an increase in aircraft acceleration, an upward aircraft speed, an increase in aircraft altitude, or a loss of contact between an aircraft landing gear and a runway.

25. The system of claim 23, wherein the sixth module determines at least one of:

an aircraft acceleration in excess of an acceleration threshold, an upward aircraft speed in excess of a speed threshold, and an increase in aircraft altitude in excess of an altitude threshold.

26. The system of claim 23, wherein the eighth module detects at least one of a go-around maneuver and contact between an aircraft landing gear and a runway.

27. The system of claim 23 comprising a ninth module that displays a pitch command after the eighth module identifies a bounce recovery.

28. The system of claim 23, wherein the bounce recovery instruction comprises a go-around instruction.

29. A pitch command display system comprising:

a first module that identifies an aircraft touchdown,

a second module that identifies an actual aircraft pitch reduction rate,

a third module that identities a target aircraft pitch reduction rate,

a pitch command module that determines a difference between the actual aircraft pitch reduction rate and the target aircraft pitch reduction rate, and that provides a pitch command when an aircraft touchdown is identified and the difference between the actual aircraft pitch reduction rate and the target aircraft pitch reduction rate is greater than a threshold amount,

a fourth module that identifies an elapsed time since aircraft touchdown, and

a display that displays the pitch command after the fourth module identifies the elapsed time.

30. The system of claim 29, wherein the display comprises a heads-up display or a primary flight display.

31. The system of claim 29, wherein the pitch command is a nose-down pitch command.

32. The system of claim 29 comprising

a fifth module that identifies an aircraft bounce,

a sixth module that determines a bounce severity,

a seventh module that determines a bounce recovery instruction based on the bounce severity, the bounce recovery instruction indicating that aircraft pitch should be maintained or that aircraft pitch should be altered, and

an eighth module that identifies a bounce recovery, wherein the display displays the instruction and discontinues display of the instruction when the eighth module identifies a bounce recovery.

33. The system of claim 32, wherein the fifth module detects at least one of:

an increase in aircraft acceleration, an upward aircraft speed, an increase in aircraft altitude, or a loss of contact between an aircraft landing gear and a runway.

34. The system of claim 32, wherein the sixth module determines at least one of:

an aircraft acceleration in excess of an acceleration threshold, an upward aircraft speed in excess of a speed threshold, and an increase in aircraft altitude in excess of an altitude threshold.

35. The system of claim 32, wherein the eighth module detects at least one of a go-around maneuver and contact between an aircraft landing gear and a runway.

36. The system of claim 32 comprising a ninth module that displays a pitch command after the eighth module identifies a bounce recovery.

37. The system of claim 32, wherein the bounce recovery instruction comprises a go-around instruction.

38. The system of claim 29, wherein the third module identifies the target aircraft pitch reduction rate based on at least one of an aircraft flap position, an aircraft slat position, and an aircraft spoiler position.

39. A pitch command display method comprising:

identifying an aircraft touchdown,

identifying a first value representing an actual aircraft pitch reduction rate,

identifying a second value representing a target aircraft pitch reduction rate,

determining a difference between the first value and the second value,

displaying a pitch command when an aircraft touchdown is identified and the difference between the first value and second value is greater than a threshold amount, and

identifying an elapsed time since aircraft touchdown, wherein displaying the pitch command comprises displaying the pitch command when the elapsed time is identified.

40. The method of claim 39, wherein displaying the pitch command comprises displaying the pitch command on a heads-up display or a primary flight display.

41. The method of claim 39, wherein the pitch command is a nose-down pitch command.

42. The method of claim 39 comprising

identifying an aircraft bounce,

determining a bounce severity,

displaying a bounce recovery instruction based on the bounce severity, the bounce recovery instruction indicating that aircraft pitch should be maintained or that aircraft pitch should be altered,

identifying a bounce recovery, and

discontinuing display of the bounce recovery instruction.

43. The method of claim 42, wherein identifying an aircraft bounce comprises at least one of:

detecting an increase in aircraft acceleration, detecting an upward aircraft speed, detecting an increase in aircraft altitude, and detecting a loss of contact between an aircraft landing gear and a runway.

44. The method of claim 42, wherein determining a bounce severity comprises determining at least one of:

an aircraft acceleration in excess of an acceleration threshold, an upward aircraft speed in excess of a speed threshold, and an increase in aircraft altitude in excess of an altitude threshold.

45. The method of claim 42, wherein identifying a bounce recovery comprises one of detecting a go-around maneuver and detecting contact between an aircraft landing gear and a runway.

46. The method of claim 42 comprising displaying a pitch command after identifying a bounce recovery.

47. The method of claim 42, wherein displaying the bounce recovery instruction comprises displaying a go-around instruction.

48. The method of claim 39, wherein identifying the second value is based on at least one of aircraft flap position, aircraft slat position, and aircraft spoiler position.

49. A pitch command display method comprising:

identifying an aircraft touchdown,

identifying a first value representing an actual aircraft pitch reduction rate,

identifying a second value representing a target aircraft pitch reduction rate of 1 degree per second,

determining a difference between the first value and the second value, and

displaying a pitch command when an aircraft touchdown is identified and the difference between the first value and second value is greater than a threshold amount.

50. The method of claim 49 comprising

identifying an aircraft bounce,

determining a bounce severity,

displaying a bounce recovery instruction based on the bounce severity, the bounce recovery instruction indicating that aircraft pitch should be maintained or that aircraft pitch should be altered,

identifying a bounce recovery, and

discontinuing display of the bounce recovery instruction.

51. The method of claim 50, wherein identifying an aircraft bounce comprises at least one of:

detecting an increase in aircraft acceleration, detecting an upward aircraft speed, detecting an increase in aircraft altitude, and detecting a loss of contact between an aircraft landing gear and a runway.

52. The method of claim 50, wherein determining a bounce severity comprises determining at least one of:

an aircraft acceleration in excess of an acceleration threshold, an upward aircraft speed in excess of a speed threshold, and an increase in aircraft altitude in excess of an altitude threshold.

53. The method of claim 50, wherein identifying a bounce recovery comprises one of detecting a go-around maneuver and detecting contact between an aircraft landing gear and a runway.

54. The method of claim 50 comprising displaying a pitch command after identifying a bounce recovery.

55. The method of claim 50, wherein displaying the bounce recovery instruction comprises displaying a go-around instruction.

56. The method of claim 49, wherein identifying the second value is based on at least one of aircraft flap position, aircraft slat position, and aircraft spoiler position.

57. The method of claim 49 comprising identifying an elapsed time since aircraft touchdown, wherein displaying the pitch command comprises displaying the pitch command when the elapsed time is identified.

58. The method of claim 49, wherein displaying the pitch command comprises displaying the pitch command on a heads-up display or a primary flight display.

59. The method of claim 49, wherein the pitch command is a nose-down pitch command.

60. The method of claim 49 comprising

identifying nose gear contact with the runway and

discontinuing display of the pitch command when nose gear contact is identified.

61. The method of claim 60 wherein the second value changes after aircraft touchdown is identified and before nose-gear contact with the runway is identified.

62. A pitch command display system comprising:

a first module that identifies an aircraft touchdown,

a second module that identifies an actual aircraft pitch reduction rate,

a third module that identities a target aircraft pitch reduction rate of 1 degree per second,

a pitch command module that determines a difference between the actual aircraft pitch reduction rate and the target aircraft pitch reduction rate, and that provides a pitch command when an aircraft touchdown is identified and the difference between the actual aircraft pitch reduction rate and the target aircraft pitch reduction rate is greater than a threshold amount, and

a display that displays the pitch command.

63. The system of claim 62 comprising

a fifth module that identifies an aircraft bounce,

a sixth module that determines a bounce severity,

a seventh module that determines a bounce recovery instruction based on the bounce severity, the bounce recovery instruction indicating that aircraft pitch should be maintained or that aircraft pitch should be altered, and

an eighth module that identifies a bounce recovery, wherein the display displays the instruction and discontinues display of the instruction when the eighth module identifies a bounce recovery.

64. The system of claim 63, wherein the fifth module detects at least one of:

an increase in aircraft acceleration, an upward aircraft speed, an increase in aircraft altitude, or a loss of contact between an aircraft landing gear and a runway.

65. The system of claim 63, wherein the sixth module determines at least one of:

an aircraft acceleration in excess of an acceleration threshold, an upward aircraft speed in excess of a speed threshold, and an increase in aircraft altitude in excess of an altitude threshold.

66. The system of claim 63, wherein the eighth module detects at least one of a go-around maneuver and contact between an aircraft landing gear and a runway.

67. The system of claim 63 comprising a ninth module that displays a pitch command after the eighth module identifies a bounce recovery.

68. The system of claim 63, wherein the bounce recovery instruction comprises a go-around instruction.

69. The system of claim 62, wherein the third module identifies the target aircraft pitch reduction rate based on at least one of an aircraft flap position, an aircraft slat position, and an aircraft spoiler position.

70. The system of claim 62 comprising a tenth module that identifies an elapsed time since aircraft touchdown, and wherein the display displays the pitch command after the tenth module identifies the elapsed time.

71. The system of claim 62, wherein the display comprises a heads-up display or a primary flight display.

72. The system of claim 62, wherein the pitch command is a nose-down pitch command.

73. The system of claim 62 comprising a fourth module that identifies when the nose gear has made contact with the runway and wherein the pitch command module discontinues providing the pitch command when the nose gear has made contact with the runway.

74. The system of claim 73, wherein the third module identifies at least two target aircraft pitch reduction rates after the first module identifies an aircraft touchdown and before the fourth module identifies the nose-gear has made contact with the runway.

75. A pitch command display method comprising:

identifying an aircraft touchdown,

identifying a first value representing an actual aircraft pitch reduction rate,

identifying a second value representing a target aircraft pitch reduction rate,

determining a difference between the first value and the second value,

displaying a pitch command when an aircraft touchdown is identified and the difference between the first value and second value is greater than a threshold amount, and

identifying nose gear contact with the runway, and

discontinuing display of the pitch command when nose gear contact is identified.

76. The method of claim 75 comprising

identifying an aircraft bounce,

determining a bounce severity,

displaying a bounce recovery instruction based on the bounce severity, the bounce recovery instruction indicating that aircraft pitch should be maintained or that aircraft pitch should be altered,

identifying a bounce recovery, and

discontinuing display of the bounce recovery instruction.

77. The method of claim 76, wherein determining a bounce severity comprises determining at least one of:

an aircraft acceleration in excess of an acceleration threshold, an upward aircraft speed in excess of a speed threshold, and an increase in aircraft altitude in excess of an altitude threshold.

78. The method of claim 76, wherein identifying a bounce recovery comprises one of detecting a go-around maneuver and detecting contact between an aircraft landing gear and a runway.

79. The method of claim 76 comprising displaying a pitch command after identifying a bounce recovery.

80. The method of claim 76, wherein displaying the bounce recovery instruction comprises displaying a go-around instruction.

81. The method of claim 76, wherein identifying an aircraft bounce comprises at least one of:

detecting an increase in aircraft acceleration, detecting an upward aircraft speed, detecting an increase in aircraft altitude, and detecting a loss of contact between an aircraft landing gear and a runway.

82. The method of claim 75 comprising identifying an elapsed time since aircraft touchdown, wherein displaying the pitch command comprises displaying the pitch command when the elapsed time is identified.

83. The method of claim 75, wherein displaying the pitch command comprises displaying the pitch command on a heads-up display or a primary flight display.

84. The method of claim 75, wherein the pitch command is a nose-down pitch command.

85. The method of claim 84 wherein the second value changes after aircraft touchdown is identified and before nose-gear contact with the runway is identified.

86. The method of claim 75, wherein identifying the second value is based on at least one of aircraft flap position, aircraft slat position, and aircraft spoiler position.

87. A pitch command display system comprising:

a first module that identifies an aircraft touchdown,

a second module that identifies an actual aircraft pitch reduction rate,

a third module that identities a target aircraft pitch reduction rate,

a pitch command module that determines a difference between the actual aircraft pitch reduction rate and the target aircraft pitch reduction rate, and that provides a pitch command when an aircraft touchdown is identified and the difference between the actual aircraft pitch reduction rate and the target aircraft pitch reduction rate is greater than a threshold amount,

a fourth module that identifies when the nose gear has made contact with the runway and wherein the pitch command module discontinues providing the pitch command when the nose gear has made contact with the runway, and

a display that displays the pitch command.

88. The system of claim 87 comprising

a fifth module that identifies an aircraft bounce,

a sixth module that determines a bounce severity,

a seventh module that determines a bounce recovery instruction based on the bounce severity, the bounce recovery instruction indicating that aircraft pitch should be maintained or that aircraft pitch should be altered, and

an eighth module that identifies a bounce recovery, wherein the display displays the instruction and discontinues display of the instruction when the eighth module identifies a bounce recovery.

89. The system of claim 88, wherein the sixth module determines at least one of:

an aircraft acceleration in excess of an acceleration threshold, an upward aircraft speed in excess of a speed threshold, and an increase in aircraft altitude in excess of an altitude threshold.

90. The system of claim 88, wherein the eighth module detects at least one of a go-around maneuver and contact between an aircraft landing gear and a runway.

91. The system of claim 88 comprising a ninth module that displays a pitch command after the eighth module identifies a bounce recovery.

92. The system of claim 88, wherein the bounce recovery instruction comprises a go-around instruction.

93. The system of claim 88, wherein the fifth module detects at least one of:

an increase in aircraft acceleration, an upward aircraft speed, an increase in aircraft altitude, or a loss of contact between an aircraft landing gear and a runway.

94. The system of claim 87 comprising a tenth module that identifies an elapsed time since aircraft touchdown, and wherein the display displays the pitch command after the tenth module identifies the elapsed time.

95. The system of claim 87, wherein the third module identifies the target aircraft pitch reduction rate based on at least one of an aircraft flap position, an aircraft slat position, and an aircraft spoiler position.

96. The system of claim 87, wherein the display comprises a heads-up display or a primary flight display.

97. The system of claim 87, wherein the pitch command is a nose-down pitch command.

98. The system of claim 97, wherein the third module identifies at least two target aircraft pitch reduction rates after the first module identifies an aircraft touchdown and before the fourth module identifies the nose-gear has made contact with the runway.