Aircraft landing gear kinetic energy monitor

• US 7,274,310 B1
• Filed: 09/13/2005
• Issued: 09/25/2007
• Est. Priority Date: 03/29/2005
• Status: Active Grant

• Current Assignee: Nance C. Kirk
• Original Assignee: Nance C. Kirk
• Inventors: Nance, C. Kirk
• Primary Examiner(s): Hofsass; Jeffery
• Assistant Examiner(s): Walk; Samuel J.
• Application Number:
  US11/225,602
• Publication Number:
  US 20070235585A1
• Time in Patent Office: 742 Days
• Field of Search: 340/960, 244/100.R, 244/102.R, 267/64.26
• US Class Current: 340/960
• CPC Class Codes: B64C 2025/008 Comprising means for modifying their length, e.g. for kneeling, for jumping, or for leveling the aircraft
• CPC Class Codes: B64C 25/00 Alighting gear air-cushion alighting gear B60V3/08
• CPC Class Codes: B64C 25/60 Oleo legs
• CPC Class Codes: B64D 2045/008 Devices for detecting or indicating hard landing
• CPC Class Codes: G01G 19/07 for weighing aircraft
• CPC Class Codes: G08B 21/00 Alarms responsive to a single specified undesired or abnormal condition and not otherwise provided for

Abstract

A system for use in monitoring, measuring, computing and displaying the Kinetic Energy generated and experienced while aircraft are executing either normal, overweight or hard landing events. Pressure sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact loads and aircraft touch-down vertical velocities experienced by landing gear struts, as the aircraft landing gear initially comes into contact with the ground. Velocity adjustments are made to correct for errors caused by landing gear per-charge pressure and landing gear strut seal friction. The system also measures the landing loads experienced by each landing gear strut during the landing event and determines if aircraft limitations have been exceeded.

Claims

1. A method of monitoring landing gear on an aircraft during a landing event of the aircraft, each landing gear comprising a telescopic strut with a compressible fluid, which telescopic strut is capable of extension, each landing gear further comprising linkage members which are capable of rotation, comprising the steps of:

a) measuring a descent velocity of the aircraft on at least one of the telescopic struts during the landing event of the respective landing gear with the ground;

b) measuring the mass of the aircraft supported by the respective landing gear as the mass increases through the landing event;

c) determining the amount of force applied to the respective landing gear from the measured descent velocity and mass;

d) providing an indication of the force.

2. The method of claim 1, wherein the step of measuring the descent velocity further comprises the step of measuring the extension of the one telescopic strut in relation to elapsed time.

3. The method of claim 2, wherein the step of measuring the extension of the one telescopic strut further comprises the step of measuring the rotation of at least one of the respective linkage members.

4. The method of claim 3 wherein the step of measuring the rotation of at least one of the linkage members further comprises the step of measuring the rotation of the one linkage member relative to an adjacent linkage member in the same landing gear, with a mechanical rotation sensor.

5. The method of claim 4 wherein the step of measuring the relative rotation of at least one of the linkage members further comprises the step of measuring the relative rotation with a rotational variable differential transformer.

6. The method of claim 4 wherein the step of measuring the relative rotation of at least one of the linkage members further comprises the step of measuring the relative rotation with a rotary potentiometer.

7. The method of claim 2 wherein the step of measuring the extension of one of the telescopic gear struts further comprises the step of measuring the inclination of one of the respective linkage members.

8. The method of claim 7 further comprising the steps of:

a) measuring the inclination of the aircraft hull before and during contact of the landing gear with the ground;

b) compensating the measured extension of the one telescopic strut with the measured aircraft hull inclinations.

9. The method of claim 8 wherein the step of measuring the increasing mass of the aircraft supported by the respective landing gear further comprises the step of measuring the pressure inside the one telescopic strut in relation to elapsed time during the landing event.

10. The method of claim 1 wherein the step of measuring the increasing mass of the aircraft supported by the respective landing gear further comprises the step of measuring the pressure inside the one telescopic strut in relation to elapsed time during the landing event.

11. The method of claim 1 further comprising the steps of:

a) determining if the amount of force applied to the respective landing gear exceeds a predetermined amount;

b) providing an indication if the amount of force exceeds the predetermined amount.

12. The method of claim 11 wherein:

a) the step of measuring the descent velocity of the aircraft on at least one of the telescopic struts further comprises the step of measuring the descent velocity of the aircraft on all of the telescopic struts;

b) the step of determining if the amount of force applied to the respective landing gear exceeds a predetermined amount further comprises the step of determining if the amount of force applied to each landing gear exceeds a predetermined amount;

c) identifying which strut has experienced an amount of force exceeding the predetermined amount.

13. The method of claim 1, further comprising the steps of:

a) measuring the aircraft hull inclination before and during contact of the respective landing gear with the ground;

b) the step of determining the amount of force further comprising the step of compensating the descent velocity with the measured aircraft hull inclinations.

14. An apparatus for monitoring landing gear of an aircraft during a landing event when the landing gear contacts the ground, each landing gear comprising a telescopic landing gear strut with a compressible fluid, each landing gear comprising a rotatable linkage, comprising:

a) a pressure sensor for each said telescopic strut, said respective pressure sensor being coupled to said respective telescopic strut so as to measure pressure inside said respective telescopic strut;

b) a rotation sensor or each said telescopic strut, said respective rotation sensor coupled to the rotatable linkage of the respective landing gear so as to measure the extension of the respective telescopic strut;

c) a processor having first inputs connected to the pressure sensors and having second inputs connected to the rotation sensors, the processor determining the amount of force applied to each landing gear during the landing event by determining the descent velocity on the respective landing gear and determining the changing amounts of mass supported by the respective landing gear and providing an output for the amount of force;

d) an indicator connected to the processor output.

15. The apparatus of claim 14 wherein the rotatable linkage comprises at least two linkages that rotate with respect to each other as the telescopic strut extends, the rotation sensor further comprises a rotary sensor that senses the rotation of the two linkages.

16. The apparatus of claim 15 wherein the rotary sensor is located at a rotatable coupling of the two linkages.

17. The apparatus of claim 14 wherein the rotatable linkage comprises at least two linkages that rotate with respect to each other as the telescopic strut extends, the rotation sensor further comprises an inclinometer coupled to one of the linkages.

18. The apparatus of claim 17 further comprising:

a) a hull inclinometer coupled to the aircraft hull;

b) the processor has an input that is connected to the hull inclinometer, the processor compensating the measurements from each inclinometer with the measurements from the hull inclinometer to determine descent velocity for each telescopic strut.

19. The apparatus of claim 14 further comprising:

a) a hull inclinometer coupled to the aircraft hull;

b) the processor has an input that is connected to the hull inclinometer, the processor compensating the measurements from each rotation sensor with the measurements from the hull inclinometer to determine descent velocity for each telescopic strut.

20. The apparatus of claim 14 wherein the processor determines if the amount of force applied to each telescopic strut exceeds a predetermined threshold and if so provides an output to the indicator.