Automated inspection of aircraft landing gear internal fluid levels
View Patent ↗A system for use in monitoring, measuring, computing and displaying the volumes of internal liquid and gas within a telescopic aircraft landing gear strut. Pressure sensors and temperature sensors and motion sensors are mounted in relation to each of the landing gear struts to monitor, measure and record the impact movement and rates of internal landing gear strut fluids; experienced by landing gear struts, as the aircraft landing gear initially come into contact with the ground. The computer of this system measures the compression experienced by each landing gear strut and determines if the landing gear strut is improperly serviced with either excess or deficient volumes of hydraulic oil and nitrogen gas. Additional features include automating the inspections required to aircraft landing gear, prior to flight, during flight and during landing events.
1. A method of monitoring internal fluid levels in a landing gear on an aircraft, the landing gear comprising a telescopic strut, the internal fluids comprising a compressible fluid and an non-compressible fluid, which telescopic strut is capable of extension, comprising the steps of:
a) exercising the strut while the aircraft is transporting passengers or cargo;
b) while the strut is exercised, allowing the strut to extend fully;
c) while the strut is exercised and fully extended, determining a measured pressure of the fluids in the strut over elapsed time;
d) determining if the measured pressure is higher than a predetermined pressure of a fully extended strut containing proper volumes of the compressed fluid and the non-compressed fluid; and
e) determining from the measured pressure the respective amounts of compressible and non-compressible fluid in the strut.
2. The method of claim 1 , wherein the step of determining from the pressure the amounts of compressible and non-compressible fluid in the strut further comprises the step of determining the amounts of compressible and non-compressible fluid from the rate of change in pressure over elapsed time.
3. The method of claim 1 , wherein the step of exercising the strut while the aircraft is transporting passengers or cargo further comprises the step of exercising the strut while the aircraft is landing.
4. The method of claim 1 , wherein the step of exercising the strut while the aircraft is transporting passengers or cargo further comprises the step of exercising the strut while the aircraft is taking off.
5. The method of claim 1 , further comprising the step of recording the respective amounts of compressible and non-compressible fluids in the strut.
6. A method of measuring the volume of leakage of a non-compressible fluid from a landing gear on an aircraft, the landing gear comprising a telescopic strut, with internal fluids comprising a compressible fluid and the non-compressible fluid, which telescopic strut is capable of extension, comprising the steps of:
a) providing a predetermined pressure of the fully extended strut containing proper volumes of the compressible fluid and the non-compressible fluid;
b) allowing the strut to fully extend under no load while the aircraft is in flight;
c) while the strut is fully extended, determining a measured pressure of the fluids in the strut;
d) determining if the measured pressure is higher than the predetermined pressure; and
e) if the measured pressure is higher than the predetermined pressure, determining from the measured pressure the volume of non-compressible fluid which has leaked from the strut.
7. The method of claim 6 , further comprising the steps of:
a) providing a look up table of pressures and corresponding ratio amounts of compressible and non-compressible fluid in the strut; and
b) the step of determining from the measured pressure the volume of non-compressible fluid which has leaked from the strut further comprising the step of using the look up table.
8. The method of claim 6 , wherein the step of allowing the strut to fully extend under no load further comprises the step of allowing the strut to extend after takeoff of the aircraft from the ground.
9. The method of claim 6 , wherein the step of allowing the strut to fully extend under no load further comprises the step of allowing the strut to extend before landing the aircraft on the ground.
10. The method of claim 6 , further comprising the step of providing an indication of the volume of non-compressible fluid which has leaked from the strut.
11. The method of claim 6 , further comprising the step of recording non-compressible fluid which has leaked from the strut.
12. The method of claim 6 , further comprising the step of determining the volume of non-compressible fluid remaining in the strut.