Landing load monitor for aircraft landing gear

• US 8,055,396 B2
• Filed: 08/23/2006
• Issued: 11/08/2011
• Est. Priority Date: 08/24/2005
• Status: Active Grant

• Current Assignee: Airbus Operations Limited (Airbus SE)
• Original Assignee: Airbus Operations Limited (Airbus SE)
• Inventors: Keen, Philip Gregory, Yates, Michael Stuart
• Primary Examiner(s): Dickson; Paul N
• Assistant Examiner(s): VERLEY, NICOLE T
• Application Number:
  US11/989,785
• Publication Number:
  US 20100161174A1
• Time in Patent Office: 1,903 Days
• Field of Search: 701/3, 701/16, 244/202, 244/203, 244/100.R, 244/102.R, 340/960
• US Class Current: 701/16
• CPC Class Codes: B64D 2045/008 Devices for detecting or indicating hard landing
• CPC Class Codes: B64D 45/00 Aircraft indicators or protectors not otherwise provided for camouflage F41H3/00
• CPC Class Codes: G01G 19/07 for weighing aircraft

Abstract

A landing gear monitor for aircraft landing gear including a plurality of pairs of wheels on a bogie, in which the main strut oil pressure serves to indicate landing load and is monitored in relation to, respectively, the two-wheel mode and the four-wheel mode, the two-wheel mode being the condition when a first of the plurality of pairs of wheels on the bogie contacts the ground and the four-wheel mode being the condition of a first and a second of the plurality of pairs of wheels on the bogie being in full contact with the ground.

Claims

1. A landing gear monitor for aircraft landing gear including a plurality of pairs of wheels on a bogie, including:

a pressure sensor which, in use, is so located in the landing gear main strut as to sense the pressure of the hydraulic fluid in the landing gear main strut, the pressure sensor providing an output electrical signal corresponding to the pressure it senses,

a first landing gear sensor for sensing and signalling that the landing gear is lowered,

a second landing gear sensor for sensing and signalling the on-set of a first mode of operation of the bogie when the bogie is in the trail position such that the first of the plurality of pairs of wheels on the bogie will contact the ground first,

a third landing gear sensor for sensing and signalling the on-set of a second mode of operation of the bogie when a second of the plurality of pairs of wheels on the bogie, in addition to the first pair of wheels, are fully engaging with the ground,

a signal processing unit connected to receive the signals from all of the sensors and, following the receipt of a signal from the first landing gear sensor indicating that the landing gear is lowered, the signal processing unit, in operation, evaluating the signals from the pressure sensor in relation to, respectively, the first mode and the second mode, and providing a main output signal indicating the results of the evaluation and

an output section connected to receive the main output signal from the signal processing unit, for providing a representation of the output signal from the signal processing unit in relation to, respectively, the first mode and the second mode.

2. A landing gear monitor as claimed in claim 1, wherein the signal processing unit includes internally stored information representing a first limiting magnitude for the signal from the pressure sensor during operation of the landing gear in the first mode, and the signal processing unit provides a first additional output signal indicative of the magnitude of the signal from the pressure sensor during the first mode relative to the first limiting magnitude.

3. A landing gear monitor as claimed in claim 2, wherein the signal processing unit includes internally stored information representing a second limiting magnitude, exceeding the first limiting magnitude, for the signal from the pressure sensor during operation of the landing gear in the first mode, and the signal processing unit provides a second additional output signal indicative of the magnitude of the signal from the pressure sensor during the first mode relative to the second limiting magnitude.

4. A landing gear monitor as claimed in claim 3, wherein the signal processing unit so operates as to capture the peak value of the signal from the pressure sensor in the first mode, and the output section so operates as to provide a representation of the peak value of the signal from the pressure sensor in the first mode in relation to the first and second limiting magnitudes.

5. A landing gear monitor as claimed in claim 2, wherein the limiting magnitudes are derived from a computer model of the landing gear.

6. A landing gear monitor as claimed in claim 1, wherein the signal processing unit includes internally stored information representing a third limiting magnitude for the signal from the pressure sensor during operation of the landing gear in the second mode, and the signal processing unit provides a third additional output signal indicative of the magnitude of the signal from the pressure sensor during the second mode relative to the third limiting magnitude.

7. A landing gear monitor as claimed in claim 1, wherein the signal processing unit includes internally stored information representing a fourth limiting magnitude, exceeding the third limiting magnitude, for the signal from the pressure sensor during operation of the landing gear in the second mode, and the signal processing unit provides a fourth additional output signal indicative of the magnitude of the signal from the pressure sensor during the second mode relative to the fourth limiting magnitude.

8. A landing gear monitor as claimed in claim 7, wherein the signal processing unit so operates as to capture the peak value of the signal from the pressure sensor in the second mode, and the output section so operates as to provide a representation of the peak value of the signal from the pressure sensor in the second mode in relation to the third and fourth limiting magnitudes.

9. A landing gear monitor as claimed in claim 1, wherein the signal processing unit so operates as to capture the peak value of the signal from the pressure sensor in the first mode.

10. A landing gear monitor as claimed in claim 1, wherein the signal processing unit so operates as to capture the peak value of the signal from the pressure sensor in the second mode.

11. A landing gear monitor as claimed in claim 1, wherein the signal processing unit, in operation, provides a main output signal, from the signal from the signal processing unit, representing the load to which the landing gear main strut is subjected.

12. A landing gear monitor as claimed in claim 11, wherein the signal processing unit includes a first lookup table relating the magnitude of the signal from the pressure sensor to the load to which the landing gear is subjected in the first mode and the main output signal from the signal processing unit is derived from the information provided by the first look-up table.

13. A landing gear monitor as claimed in claim 11, wherein the signal processing unit includes a second look-up table relating the magnitude of the signal from the pressure sensor to the load to which the landing gear is subjected in the second mode and the main output signal from the signal processing unit is derived from the information provided by the second look-up table.

14. A landing gear monitor as claimed in claim 1, wherein the signal processing unit samples the signal from the pressure sensor at intervals of about 20 milliseconds.

15. A landing gear monitor as claimed in claim 1 for and operable with a four-wheel bogie.

16. A landing gear monitor as claimed in claim 1, wherein a landing gear articulation sensor performs the functions of the second and third landing gear sensors.

17. An aircraft landing gear including a landing gear monitor as claimed in claim 1.

18. An aircraft including a landing gear monitor as claimed in claim 1.

19. A computer program for operating a landing gear monitor as claimed in claim 1.

20. A method of operation of a landing gear monitor for aircraft landing gear including a plurality of pairs of wheels on a bogie, including:

sensing the pressure of the hydraulic fluid in the landing gear main strut and providing an output electrical signal corresponding to the sensed pressure, sensing and signalling that the landing gear is lowered, sensing and signalling when the bogie is in the trail position, the condition of the bogie being in the trail position being identified hereinafter as the first mode, sensing and signalling when a second of the plurality of pairs of wheels on the bogie, in addition to the first pair of wheels, fully engages with the ground, the condition of a first and a second of the plurality of pairs of wheels on the bogie fully engaging with the ground being identified hereinafter as the second mode, evaluating the signals from the sensing of the pressure of the hydraulic fluid in relation to, respectively, the first mode and the second mode, and providing a main output signal indicating the results of the evaluation and providing a representation of the main output signal in relation to, respectively, the first mode and the second mode.

21. A landing gear monitor programmed to operate in accordance with a method as claimed in claim 20.