Sensor for measuring large mechanical strains with fine adjustment device

• US 8,627,727 B2
• Filed: 07/19/2010
• Issued: 01/14/2014
• Est. Priority Date: 07/19/2010
• Status: Active Grant

• Current Assignee: Goodrich Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Eriksen, Odd Harald Steen, Stang, Lawrence Joseph, Guo, Shuwen
• Primary Examiner(s): Dinh, Tien
• Assistant Examiner(s): Green, Richard R
• Application Number:
  US12/839,401
• Publication Number:
  US 20120012701A1
• Time in Patent Office: 1,275 Days
• Field of Search: 244/100.R, 244/102.R, 244/102.A, 244/102.SL, 244/102.SS, 737/80, 738/626.26
• 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.

Claims

1. A capacitive strain sensor for sensing strain, comprising:

a first cap configured and adapted to be attached to a structure at a first location, the first cap including a first capacitor plate mounted thereto configured and adapted to be electronically isolated from the structure, the first cap having an inboard end proximate the first capacitor plate;

a second cap configured and adapted to be attached to the structure at a second location, the second cap including a second capacitor plate mounted thereto configured and adapted to be electronically isolated from the structure, the second cap having an inboard end opposed to the inboard end of the first cap; and

a flexible component between and connecting the opposed inboard ends of the first and second caps,

wherein the first capacitor plate is separated from the second capacitor plate by a capacitive gap,

wherein a normal vector to respective surfaces of the capacitive plates is approximately parallel to a longitudinal axis of the sensor,

wherein the longitudinal axis of the sensor is approximately parallel with direction of strain to be measured, and

wherein the first and second caps are configured such that strain experienced by the structure causes a change in the capacitive gap due to relative motion between the first and second capacitor plates of the first and second caps.

2. The sensor of claim 1, wherein the component comprises at least one of a pleated or convoluted expandable component.

3. The sensor of claim 2, wherein the first and second caps and the flexible component provide a hermetic seal of at least one of the capacitive plates and an interior of the first cap.

4. The sensor of claim 2, wherein the flexible component is bonded by a weld to the first and second caps.

5. The sensor of claim 1, wherein the first capacitor plate comprises an insulator at least partially covered with a metallic coating, wherein the second capacitor plate comprises an insulator at least partially covered with a metallic coating.

6. The sensor of claim 1, further comprising:

a cavity located in at least one of the first and second caps;

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.

7. The sensor of claim 1, further comprising:

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

a second structure attachment point connected to the second cap,

wherein the first and second attachment points are connected at approximately a same radial location on the first and second caps.

8. The sensor of claim 1, further comprising a means for adjusting the gap.

9. The sensor of claim 8, wherein the second cap comprises a housing having at least a partially threaded inner wall having a first threads-per-inch value and a core having at least a partially threaded outer wall having a second threads-per-inch value, wherein the means for adjusting comprises a ring having a threaded outer wall having the first threads-per-inch value and a threaded inner wall having the second threads-per-inch value.

10. The sensor of claim 9, further comprising a device for restricting rotational movement of the ring.

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

12. The sensor of claim 11, wherein the means for adjustably attaching comprises at least one dowel received by one of the first and second caps, and a tapered dowel received within at least one cavity within at least one of the first and second caps and 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 and the torque linkage, the sensor including

a first cap attached to the at least one of the strut piston and the torque linkage at a first location, the first cap having an inboard end and a capacitor plate electronically isolated from the at least one of the strut piston and the torque linkage,

a second cap attached to the at least one of the strut piston and the torque linkage at a second location, the second cap having an inboard end opposed to the inboard end of the first cap and a capacitor plate electronically isolated from the at least one of the strut piston and the torque linkage, and

a flexible component between and connecting the opposed inboard ends of the first and second caps,

wherein the capacitor plate of the first cap is separated from the capacitor plate of the second cap by a capacitive gap, wherein a normal vector to respective surfaces of the capacitive plates is approximately parallel to a longitudinal axis of the sensor.

14. The landing gear assembly of claim 13, wherein the first and second caps are configured such that strain experienced by at least one of the strut piston and the torque linkage causes a change in the capacitive gap due to relative motion between the first and second caps.

15. The landing gear assembly of claim 14, wherein the flexible component is bonded by a weld to at least one of the first and second caps.

16. The landing gear assembly of claim 13, wherein the sensor further comprises a means for adjusting the gap.

17. The landing gear assembly of claim 16, wherein the second cap comprises a housing having at least a partially threaded inner wall having a first threads-per-inch value and a core having at least a partially threaded outer wall having a second threads-per-inch value, wherein the means for adjusting comprises a ring having a threaded outer wall having the first threads-per-inch value and an threaded inner wall having the second threads-per-inch value.

18. The landing gear assembly of claim 17, wherein the sensor further comprises a device for restricting rotational movement of the ring.