Method for monitoring an aircraft landing gear employing at least one accelerometer supported by a wheel of the landing gear, and aircraft implementing this method

Patent metadata

Field	Value
Publication number	US-12371157-B2
Application number	US-202218561048-A
Country	US
Kind code	B2
Filing date	May 18, 2022
Priority date	May 19, 2021
Publication date	Jul 29, 2025
Grant date	Jul 29, 2025

Abstract

A method for monitoring an aircraft landing gear. The method includes using information from at least one accelerometer firmly secured to a landing gear wheel mounted to rotate on a landing gear axle to estimate an angle of deflection α of the axle at least when the wheel is in contact with the ground.

First claim

The invention claimed is:

1. A method of monitoring an aircraft landing gear having a device for monitoring the pressure of a tire, the tire being carried by a wheel of the landing gear, the wheel being mounted to rotate on a landing gear axle, the method comprising:
estimating an angle of deflection α of the axle at least when the wheel is in contact with the ground, wherein the estimation uses information from at least one accelerometer integrated into the pressure monitoring device.

2. The method according to claim 1 , wherein a transverse acceleration γ y,c measured by the accelerometer in a direction substantially parallel to a central axis of the axle and dependent on the angle of deflection α of the axle is used to estimate the angle of deflection α of the axle.

3. The method according to claim 2 , wherein an angle β of rotation of the wheel is estimated from an orthoradial acceleration γ x,c and/or a radial acceleration γ z,c measured by the accelerometer, and a speed of rotation ω=β{dot over ( )} is then estimated, wherein the two estimates are utilized to eliminate from the transverse acceleration γ y,c terms varying with the angle of rotation and the speed of rotation, and then the angle of deflection α of the axle is estimated from the transverse acceleration γ y,c thus reprocessed.

4. The method according to claim 2 , further comprising filtering the transverse acceleration γ y,c and a radial acceleration γ z,c measured by the accelerometer to obtain a filtered transverse acceleration γ y,c,f and a filtered radial acceleration γ z,c,f by eliminating the terms varying periodically as a function of an angle of rotation β of the wheel.

5. The method according to claim 4 , wherein the filtering is started from a landing onset that is detected when the quantity |γ z,c | exceeds a threshold or is in saturation.

6. The method according to claim 4 , wherein, after the filtering has been established, the method further comprises:
collecting the data

y
i

=

γ

y
,
c
,
f

(

t
i

)

⁢

h
⁡
(

t
i

)

=

[

1

γ

y
,
c
,
f

⁢

(

t
i

)

]

.

where the t i are the sampling instants, γ y,c,f is the filtered transverse acceleration, and γ z,c,f is the filtered radial acceleration;
arranging the sampled data into the following matrix form:

Y
=

[

y
1

…

y
n

]

H
=

[

h
1

…

h
n

]

estimating a state vector X by calculating {circumflex over (X)}=M·Y with the pseudo-inverse M=(H t ·H) −1 ·H t ; and
estimating the angle of deflection of the axle by calculating {circumflex over (α)}=arcsin ({circumflex over (X)}(1)/g) where g is the acceleration of gravity.

7. The method according to claim 6 , wherein the pseudo-inverse calculation is replaced by a recursive least-squares method.

8. The method according to claim 4 , further comprising calculating a corrected acceleration (γ y,c,cor ) from the filtered accelerations γ y,c,f and γ z,c,f :

γ

y
,
c
,
cor

≈

γ

y
,
c
,
f

-

θ

y
⁢
z

⁢

γ

z
,
c
,
f

Assignees

• Safran Electronics & Defense
• Safran Landing Systems

Inventors

• Zabulon Joël
• Lekarski Kyril
• Fanton Nicolas
• Michaud Benjamin
• Brunstein Etienne

Classifications

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• B64D2045/008

  Devices for detecting or indicating hard landing · CPC title

• B64C25/001

  Devices not provided for in the groups B64C25/02 - B64C25/68 · CPC title

• G01B21/26

  for testing wheel alignment · CPC title

• B64C25/28 Primary

  with indicating or warning devices · CPC title