Sensor for measuring large mechanical strains in shear or lateral translation

• US 8,607,640 B2
• Filed: 07/19/2010
• Issued: 12/17/2013
• Est. Priority Date: 07/19/2010
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Original Assignee: Goodrich Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: Eriksen, Odd Harald Steen
• Primary Examiner(s): Sanderson, Joseph W
• Assistant Examiner(s): Xavier, Valentina
• Application Number:
  US12/839,061
• Publication Number:
  US 20120012699A1
• Time in Patent Office: 1,247 Days
• Field of Search: 244/100.R, 737/291, 737/18, 737/80
• US Class Current: 73/780
• CPC Class Codes: B64D 2045/008 Devices for detecting or indicating hard landing
• CPC Class Codes: G01B 7/22 using change in capacitance
• CPC Class Codes: G01L 1/142 using capacitors
• CPC Class Codes: G01L 5/0052 measuring forces due to impact G01L5/0061, G01L5/14 take precedence; impact testing of structures G01M7/08; impact testing of material G01N3/00

Abstract

A capacitive strain sensor for sensing strain of a structure. The sensor includes a first section attached to the structure at a first location and a second section attached to the structure at a second location. The first section includes a capacitor plate electrically isolated from the structure and the second section includes two electrically isolated capacitive plates, both of the plates being electrically isolated from the structure. A flexible connector connects the first section to the second section. The capacitor plate of the first section is separated from the two capacitive plates of the second section by at least one capacitive gap. When strain is experienced by the structure, a change occurs in the capacitive gap due to relative motion between the first and second sections. The first section includes a core and the second section includes a ring that receives the core.

Claims

1. A capacitive strain sensor for sensing strain of a structure, the sensor comprising:

a first section attached to the structure at a first location, the first section comprising a capacitor plate electrically isolated from the structure, wherein the first section is a core having an outer diameter, and wherein the capacitor plate is mounted to the core;

a second section attached to the structure at a second location, the second section comprising two electrically isolated capacitive plates, both of the plates being electrically isolated from the structure, wherein the second section is a ring having an inner diameter greater than the outer diameter of the core and the two electrically isolated capacitive plates are mounted to the ring; and

a component configured to flexibly connect the first section to the second section,

wherein the capacitor plate of the first section is separated from the two capacitive plates of the second section by at least one capacitive gap, and wherein the first section is axially movable relative to the second section.

2. The sensor of claim 1, further comprising a device configured to flexibly connect the first and second sections,

wherein strain experienced by the structure causes a change in the at least one capacitive gap due to relative motion between the first and second sections.

3. The sensor of claim 2, wherein the device comprises at least one of pleated or convoluted expandable component.

4. The sensor of claim 3, wherein the first section, the second section, and the device provide a hermetic seal of at least one of the capacitive plates or the interior of the sensor.

5. The sensor of claim 3, wherein the device comprises at least two hinged metal annuli and the device is bonded by a weld to the first and second sections.

6. The sensor of claim 1, wherein the capacitor plate of the first section includes a metallic coating at least partially covering the core, wherein the two capacitive plates of the second section include two respective metallic coatings at least partially covering the ring.

7. The sensor of claim 6, further comprising:

a first structure attachment point connected to the first section; and

a second structure attachment point connected to the second section,

wherein the first and second attachment points are connected at approximately the same radial location on the first and second sections,

wherein the two metallic coatings on the ring are electrically isolated from each other and a first one of the two metallic coatings is located on a first half of the ring with an end near the attachment points and the second of the two metallic coatings is located on a second half of the ring with an end near the attachment points.

8. The sensor of claim 6, wherein the core and ring have dimensions along a longitudinal axis, wherein the dimension of the core is greater than the dimension of the ring.

9. The sensor of claim 6, wherein the ring is centered at a longitudinal center of the sensor.

10. The sensor of claim 1, further comprising:

a cavity located in at least one of the first or second sections;

at least one circuit component located in the cavity; and

electrical leads configured to connect the at least one circuit component to the capacitive plates.

11. The sensor of claim 1, further comprising a means for adjustably attaching the first and second sections to the structure.

12. The sensor of claim 11, wherein the means for adjustably attaching comprises one or more tapered eccentric dowels received by one of the first or second sections, cavities within the structure, and a tapered dowel received within at least one cavity within at least one of the first or second sections or the structure.

13. A landing gear assembly comprising:

a strut piston;

a torque linkage; and

a capacitive strain sensor for sensing strain of at least one of the strut piston or the torque linkage, the sensor comprising;

a first section attached to the at least one of the strut piston or the torque linkage at a first location, the first section comprising a capacitor plate electrically isolated from the at least one of the strut piston or the torque linkage, wherein the first section is a core having an outer diameter, and wherein the capacitor plate is mounted to the core;

a second section attached to the at least one of the strut piston or the torque linkage at a second location, the second section comprising two electrically isolated capacitive plates, both of the plates being electrically isolated from the at least one of the strut piston or the torque linkage, wherein the second section is a ring having an inner diameter greater than the outer diameter of the core and the two electrically isolated capacitive plates are mounted to the ring; and

a component configured to flexibly connect the first section to the second section, wherein the first section is axially movable relative to the second section, and

wherein the capacitor plate of the first section is separated from the two capacitive plates of the second section by at least one capacitive gap.

14. The landing gear assembly of claim 13, wherein the sensor further comprises a device configured to flexibly connect the first and second sections,

wherein strain experienced by the at least one of the strut piston or the torque linkage causes a change in the at least one capacitive gap due to relative motion between the first and second sections.

15. The landing gear assembly of claim 14, wherein the device comprises pleated expandable component, wherein the first section, the second section, and the device provide a hermetic seal of the capacitive plates.

16. The landing gear assembly of claim 15, wherein the device comprises at least two hinged metal annuli and the device is bonded by a weld to the first and second sections.

17. The sensor of claim 13, wherein the capacitor plate of the first section includes a metallic coating at least partially covering the core, wherein the two capacitive plates of the second section include two respective metallic coatings at least partially covering the ring.

18. The landing gear assembly of claim 17, wherein the sensor further comprises:

a first structure attachment point connected to the first section; and

a second structure attachment point connected to the second section,

wherein the first and second attachment points are connected at approximately the same radial location on the first and second sections,

wherein the two metallic coatings on the ring are electrically isolated from each other and the two metallic coatings are located on a half of the ring starting on opposite sides of the attachment points.

19. The landing gear assembly of claim 17, wherein the core and ring have dimensions along a longitudinal axis, wherein the dimension of the core is greater than the dimension of the ring, wherein the ring is centered at a longitudinal center of the sensor.

20. The landing gear assembly of claim 13, wherein the sensor further comprises a means for adjustably attaching the first and second sections to the at least one of the strut piston or the torque linkage.