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

Patent metadata

Field	Value
Publication number	US-9879973-B2
Application number	US-201514972987-A
Country	US
Kind code	B2
Filing date	Dec 17, 2015
Priority date	Dec 18, 2014
Publication date	Jan 30, 2018
Grant date	Jan 30, 2018

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

The invention claimed is:

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 mounting structure for mounting the measurement device on the first part, the mounting structure being fixed around the first part;
a plurality of blades, each blade comprising a first end, which is secured to the mounting structure, and a second end, which is for bearing either on a surface of the second part or on a surface of an intermediate member of the measurement device, wherein the intermediate member is for mounting around the second part, wherein the plurality of blades comprises three or more blades, and wherein the plurality of blades are distributed around a central axis of the measurement device;
at least one strain/deformation sensor associated with each blade, the at least one strain/deformation sensor being configured to transmit output signals dependent on levels of deformation of a respective one of the plurality of blades; and
a conversion unit configured to deliver, from the output signals of the strain/deformation sensors, at least one datum corresponding to a relative position of the first and second parts, including an axial displacement between the first and second parts.

2. The measurement device according to claim 1 , wherein the conversion unit is configured to deliver, from the output signals of the strain/deformation sensors, at least one datum corresponding to a 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 , wherein the intermediate member has an outer surface that is tapered, with a section that narrows 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 for delivering a temperature signal to the conversion unit.

7. The measurement device according to claim 1 , wherein the at least one strain/deformation sensor is at least one fiber optic strain gauge or at least one electrical strain gauge.

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 of measuring displacement between a first part and a second part mounted on one another and arranged substantially coaxially, the method comprising:
providing a measurement device for measuring displacement between the first part and the second part, which are mounted on one another and arranged substantially coaxially with each other, the measurement device comprising:
a mounting structure for mounting the measurement device on the first part, the mounting structure being fixed around this first part;
a plurality of blades, each blade comprising a first end, which is secured to the mounting structure, and a second end, which is for bearing either on a surface of the second part or on a surface of an intermediate member of the measurement device, wherein the intermediate member is for mounting around the second part, wherein the plurality of blades comprises three or more blades, and wherein the plurality of blades are distributed around a central axis of the measurement device;
at least one strain/deformation sensor associated with each blade, the at least one strain/deformation sensor being configured to transmit output signals dependent on levels of deformation of a respective one of the plurality of blades; and
a conversion unit configured to deliver, from the output signals of the strain/deformation sensors, at least one datum corresponding to a relative position of the first and second parts, including an axial displacement between the first and second parts; and

determining at least one datum corresponding to the relative position of the first and second parts from the output signals of the at least one strain/deformation sensor, associated with a respective one of the plurality of blades, of the measurement device.

Assignees

• Airbus Operations Sas

Inventors

• Boisson Thomas

Classifications

• G01B11/18

  using photoelastic elements · CPC title

• G01B11/16

  for measuring the deformation in a solid, e.g. optical strain gauge · CPC title

• B64D2045/0085

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

• B64D37/005

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

• G01B5/25

  for testing the alignment of axes · CPC title