Method for adjusting the angular position of a wheel, in particular a wheel of an aircraft landing gear

Patent metadata

Field	Value
Publication number	US-12304622-B2
Application number	US-202118008369-A
Country	US
Kind code	B2
Filing date	May 31, 2021
Priority date	Jun 25, 2020
Publication date	May 20, 2025
Grant date	May 20, 2025

Abstract

A method for adjusting the angular position of a wheel, in particular a wheel of a landing gear on an aircraft. The wheel being connected to at least one hydraulic cylinder controlled by a servo valve. The method comprising a step for determining an angular deviation between a measurement of the angular position and a setpoint angular position, a first proportional correction step, a second integral correction step and a step for adding the first current and the second current in order to determine a control current of the servo valve. The second integral control step comprising a sub-step for limiting the second current according to a parametric law imposing a second current of zero value when the angular deviation is less, in absolute value, than a first determined threshold.

First claim

The invention claimed is:

1. A method for adjusting an angular position of a wheel, the wheel being connected to at least one hydraulic cylinder controlled by a servo valve, the method comprising:
a step to determine an angular difference between a measurement of the angular position and a setpoint angular position,
a first proportional correction step in order to determine a first current from an angular deviation,
a second integral correction step in order to determine a second current from the angular deviation,
an addition step of the first current and the second current in order to determine a control current of the servo valve, wherein
the second integral adjustment step comprises a sub-step limiting the second current according to a parametric law, the parametric law imposing a second current of zero value when the angular deviation is less, in absolute value, than a first determined angular threshold.

2. The method for adjusting according to claim 1 , wherein the parametric law limits the second current to a maximum allowed current value when the angular deviation is between, as an absolute value, the second determined angular threshold and a third determined angular threshold, wherein the second determined angular threshold and the third determined angular threshold is greater than the first determined angular threshold.

3. The method for adjusting according to claim 2 , wherein the parametric law limits the second current according to an ascending ramp between the zero value and the maximum allowed current value when the angular deviation is between, as an absolute value, the first determined angular threshold and the second determined angular threshold.

4. The method for adjusting according to claim 2 , wherein the parametric law limits the second current according to a downward ramp between the maximum allowed current value and the zero value when the angular deviation is between, as an absolute value, the third determined angular threshold and a fourth determined angular threshold greater than the third determined threshold.

5. A wheel angular position control system connected to at least one hydraulic cylinder controlled by a servo valve, the control system comprising a calculator configured to:
determine an angular difference between a measurement of an angular position and a setpoint angular position,
make a first proportional correction in order to determine a first current from the angular difference,
perform a second integral correction in order to determine a second current from an angular deviation,
sum the first current and the second current to determine a control current of the servo valve, and
when performing the second integral correction, limit the second current according to a parametric law, the parametric law imposing a second current of zero value when the angular difference is less, in absolute value, than a first determined angular threshold.

6. An assembly of a wheel connected to the at least one hydraulic cylinder controlled by servo valve and the control system according to claim 5 for determining the control current of the servo valve.

7. The assembly according to claim 6 , wherein the at least one hydraulic cylinder includes a first hydraulic cylinder and a second hydraulic cylinder, and wherein the wheel is connected to the at least one of the first hydraulic cylinder and the second hydraulic cylinder controlled by the servo valve.

8. The assembly according to claim 6 , further comprising a hydraulic module, comprising the servo valve, wherein the at least one hydraulic cylinder includes a first hydraulic cylinder and a second hydraulic cylinder, the servo valve being configured to directly control the first hydraulic cylinder and the second hydraulic cylinder.

9. Aircraft landing gear comprising the assembly according to claim 6 .

10. An aircraft comprising the gear according to claim 9 .

Assignees

• Safran Landing Systems

Inventors

• Mazzane Ismail

Classifications

• B64C25/22

  fluid · CPC title

• Y02T50/80

  Energy efficient operational measures, e.g. ground operations or mission management · CPC title

• B64C25/50 Primary

  Steerable undercarriages; Shimmy-damping · CPC title

• B64C25/505 Primary

  Shimmy damping · CPC title