Granted Patent B2

US 12,420,916 · App. 18/570,500 · Granted Sep 23, 2025

Inventors: Nicolas Nguyen (Moissy-Cramayel, FR); Bertrand Dubacher (Moissy-Cramayel, FR)

Assignee: SAFRAN LANDING SYSTEMS

B64C25/001B64C25/10G01B11/26

Abstract

Claims (33)

1. An aircraft landing gear comprising:

a stationary element and at least one movable element which can move relative to the stationary element between a first position and a second position, and detection means arranged to detect when the movable element is in at least one of its positions,

wherein the detection means comprise at least one threadlike and flexible shape sensor, connected to an electronic processing unit arranged to deduce the position of the movable element of the shape of the shape sensor, and

the shape sensor comprising a first section rigidly connected to the stationary element and a second section rigidly connected to the movable element so that the first section and the second section are immobile with respect to the stationary element and the movable element respectively, and are movable relative to one another.

2. The aircraft landing gear according to claim 1 , wherein the shape sensor is an optical fibre shape sensor.

3. The aircraft landing gear according to claim 2 , wherein the shape sensor comprises a Bragg grated optical fibre.

4. A method for measuring, at a time t, a stroke of the rod of the aircraft landing gear according to claim 2 , wherein the electronic processing unit is configured to:

when said rod is in a relaxed extreme position, determine and record from a light signal introduced in the shape sensor a reference position about the axis of a measuring point of the second section of the shape sensor;

at the time, determine a position of the measuring point from the light signal introduced in the shape sensor;

calculate a difference between the reference position and the position at the time; and

deduce from the difference, a stroke function C(t) of the rod at the time t.

5. The aircraft landing gear according to claim 1 , wherein the shape sensor comprises a WDM-type wavelength division multiplexing optical fibre.

6. The aircraft landing gear according to claim 1 , wherein the shape sensor comprises an OFDR-type frequency domain reflectometry optical fibre.

7. The aircraft landing gear according to claim 1 , further comprising a strut comprising a box,

wherein a rod is slidingly mounted about an axis, a lower end of which carries wheels, and a rotating sleeve surrounding a lower part of the box and connected by a compass articulated to the sliding rod, the first section and the second section of the shape sensor being respectively rigidly connected to the box and to the rod.

8. A method for measuring, at a time t, an angular position of the rod of the landing gear according to claim 7 , wherein the electronic processing unit is configured to:

when the wheels are oriented about a longitudinal axis of the aircraft, determine and record from a light signal introduced in the shape sensor a reference position of a measuring point of the second section of the shape sensor;

at the time t, determine the position of the measuring point from the light signal introduced in the shape sensor;

calculate the angle formed by the reference position and the position at the time t with respect to the sliding axis of the rod; and

deduce from the angle the angular position of the rod at the time t.

9. A method for measuring, at a time t, an angular position of the rod of the aircraft landing gear according to claim 7 , wherein the electronic processing unit is configured to:

when the wheels are oriented about a longitudinal axis of the aircraft, determine and record from a light signal introduced in the shape sensor reference positions of at least two measuring points of the second section of the shape sensor arranged in a plane orthogonal to the sliding axis of the rod;

at the time t, determining positions of the measuring points from the light signal introduced in the shape sensor; and

calculating the angle formed by the straight line defined by the reference positions and the straight line defined by the positions at the time t; and

deduce from the angle, the angular position of the rod at the time t.

10. The aircraft landing gear according to claim 1 , further comprising a strut comprising a box,

wherein the shape sensor comprises an optical fibre, and

wherein a rod is slidingly mounted about an axis, a lower end of which carries wheels, and a rotating sleeve surrounding a lower part of the box and connected by a compass articulated to the sliding rod, the first section and the second section of the optical fibre being respectively rigidly connected to the box and to the compass.

11. A method for measuring, at a time t, a stroke of the rod of the aircraft landing gear according to claim 10 , wherein the compass comprises an upper branch articulated on the sleeve and a lower branch articulated on the upper branch and on the rod, the upper branch and the lower branch defining an opening angle of the compass and the electronic processing unit being configured to:

when said rod is in a relaxed extreme position, determine and record from a light signal introduced in the shape sensor a reference opening angle of the compass;

at the time, determining the opening angle of the compass from the light signal introduced in the shape sensor;

calculate a difference between the reference opening angle and the opening angle at the time; and

deduce from the difference a stroke function C(t) at the time t of the rod by trigonometry.

Assignments (1)

Priority Claims (1)

Continuity (1)

References Cited (13)