Device and method for measuring displacement between two substantially coaxial parts, preferably for aircraft

Patent metadata

Field	Value
Publication number	US-2016178342-A1
Application number	US-201514972987-A
Country	US
Kind code	A1
Filing date	Dec 17, 2015
Priority date	Dec 18, 2014
Publication date	Jun 23, 2016
Grant date	—

Abstract

A device and method of simple design for measuring displacement between a first part and a second part that are substantially coaxial, preferably mounted on one another by an annular linear link. The device includes a structure for mounting the device on the part, blades secured to the structure and bearing on an outer surface of an intermediate member, the member being mounted around the part, at least one strain/deformation sensor associated with each blade, the sensors configured to transmit output signals dependent on the levels of deformation of the blades, and a conversion unit configured to deliver, from the output signals, at least one datum corresponding to the relative position of the parts, preferably out of an azimuth angle, an elevation angle and an axial displacement.

First claim

1 . A measurement device for measuring displacement between a first part and a second part mounted on one another and arranged substantially coaxially, the measurement device comprising:
a structure for mounting the device on the first part, the mounting structure being fixed around this first part; a plurality of blades, each blade comprising a first end secured to the mounting structure and a second end for bearing either on a surface of the second part, or on a surface of an intermediate member of the device, the intermediate member being for mounting around the second part, the blades being provided in a number greater than or equal to three and distributed around a central axis of the measurement device; at least one strain/deformation sensor associated with each blade, the sensors being configured to transmit output signals dependent on levels of deformation of the blades; and a conversion unit configured to deliver, from the output signals of the strain/deformation sensors, at least one datum corresponding to the relative position of the first and second parts, including an axial displacement between the two parts.

2 . The measurement device according to claim 1 , wherein the conversion unit is configured to also deliver, from the output signals of the strain/deformation sensors, at least one datum corresponding to the relative position of the first and second parts out of an azimuth angle and an elevation angle.

3 . The measurement device according to claim 1 , wherein the surface of the second part is an outer surface of the second part, and wherein the surface of the intermediate member is an outer surface of the intermediate member.

4 . The measurement device according to claim 1 , comprising the intermediate member of which the outer surface is tapered, of section narrowing towards the first part.

5 . The measurement device according to claim 1 , comprising a linear displacement sensor for delivering the datum corresponding to the axial displacement between the first and second parts.

6 . The measurement device according to claim 1 , comprising a temperature sensor delivering a temperature signal to the conversion unit.

7 . The measurement device according to claim 1 , wherein the strain/deformation sensors are fiber optic strain gauges or electrical strain gauges.

8 . The measurement device according to claim 1 , wherein the mounting structure and/or the intermediate member are each produced from a number of angular sectors mounted on one another.

9 . The measurement device according to claim 1 , wherein the first and second parts are fitted into one another, so as to form an annular linear link.

10 . An assembly for aircraft comprising a first part and a second part mounted on one another and arranged substantially coaxially, and a measurement device according to claim 1 , cooperating with the first and second parts.

11 . The assembly according to claim 10 , wherein the first and second parts are tubular, and of circular section.

12 . The assembly according to claim 10 , wherein the first and second parts are two ducts, or a duct and a duct coupling.

13 . The assembly according to claim 10 , forming an integral part of a fuel feed system.

14 . An aircraft comprising at least one assembly according to claim 10 .

15 . A method for measuring displacement between a first part and a second part mounted on one another and arranged substantially coaxially, the method implemented using a measurement device for measuring displacement between a first part and a second part mounted on one another and arranged substantially coaxially, the measurement device comprising:
a structure for mounting the device on the first part, the mounting structure being fixed around this first part; a plurality of blades, each blade comprising a first end secured to the mounting structure and a second end for bearing either on a surface of the second part, or on a surface of an intermediate member of the device, the intermediate member being for mounting around the second part, the blades being provided in a number greater than or equal to three and distributed around a central axis of the measurement device; at least one strain/deformation sensor associated with each blade, the sensors being configured to transmit output signals dependent on levels of deformation of the blades; and a conversion unit configured to deliver, from the output signals of the strain/deformation sensors, at least one datum corresponding to the relative position of the first and second parts, including an axial displacement between the two parts; and the method comprising determining at least one datum corresponding to the relative position of the first and second parts, from the output signals of the strain/deformation sensors associated with the blades of the measurement device.

Assignees

• Airbus Operations Sas

Inventors

• Boisson Thomas

Classifications

• B64D37/005

  Accessories not provided for in the groups B64D37/02 - B64D37/28 · CPC title

• G01B11/18

  using photoelastic elements · CPC title

• G01B5/25

  for testing the alignment of axes · CPC title

• F16L2201/10

  Indicators for correct coupling · CPC title

• F16L27/1017

  Joints with sleeve or socket · CPC title