System for sensing miniature gaps by inductive coupling

Patent metadata

Field	Value
Publication number	US-11801946-B2
Application number	US-201916394278-A
Country	US
Kind code	B2
Filing date	Apr 25, 2019
Priority date	Apr 25, 2019
Publication date	Oct 31, 2023
Grant date	Oct 31, 2023

Abstract

Systems and methods for measuring air gaps between opposing surfaces of two structural components. In one application, such measurements are used to fabricate a shim that fills the air gap between two structural members, such as parts of an aircraft. The resonant inductive coupling-based sensing system has the capability to remotely measure an air gap using an on-board transmit system. Furthermore, the system has the capability to switch between multiple inductor-capacitor sets such as to simultaneously measure air gaps across an area so that a better profile of the air gap can be determined. The resonant inductive coupling-based gap sensor is configured as signal generating and signal sensing electronics printed or mounted on respective flexible substrates to provide a flexible and portable measurement solution.

First claim

The invention claimed is:

1. A system for measuring an air gap between first and second surfaces, comprising:
a first flexible substrate adhered to the first surface;
a first LC circuit supported by the first flexible substrate and comprising a first inductor and a first capacitor;
a signal generator electrically connected to the first LC circuit;
a second flexible substrate adhered to the second surface;
a second LC circuit supported by the second flexible substrate and comprising a second inductor and a second capacitor;
a signal processor electrically connected to the second LC circuit; and
a transmit antenna electrically connected to the signal processor, wherein the first inductor is aligned with the second inductor.

2. The system as recited in claim 1 , further comprising a half-wave rectifier that converts alternating current from the second LC circuit into direct current that is received by the signal processor.

3. The system as recited in claim 2 , wherein the signal processor is configured to convert analog signals from the half-wave rectifier into digital signals.

4. The system as recited in claim 2 , wherein the signal processor and half-wave rectifier are surface mounted on the second flexible substrate.

5. The system as recited in claim 4 , wherein the transmit antenna is disposed on the second flexible substrate.

6. The system as recited in claim 1 , wherein the signal processor is configured to receive electric power from the transmit antenna.

7. The system as recited in claim 1 , wherein the first flexible substrate comprises first and second dielectric layers adhered to each other, the first inductor is disposed on the first dielectric layer, the first capacitor comprises one electrode disposed on the first dielectric layer and electrically connected to the first inductor and another electrode disposed between the first and second dielectric layers.

8. The system as recited in claim 7 , wherein the second flexible substrate comprises third and fourth dielectric layers adhered to each other, the second inductor is disposed on the third dielectric layer, the second capacitor comprises one electrode disposed on the third dielectric layer and electrically connected to the second inductor and another electrode disposed between the third and fourth dielectric layers and electrically connected to the second conductor.

9. The system as recited in claim 1 , further comprising a receive antenna, a digital signal processor configured to output digital gap size data which represents an air gap profile and is a function of digital gap sensor measurement data received by the receive antenna, a non-transitory tangible computer-readable storage medium for storing the gap size data output by the digital signal processor, and a display device for displaying symbology representing the air gap profile in response to retrieval of the gap size data from the non-transitory tangible computer-readable storage medium.

10. The system as recited in claim 1 , further comprising a third LC circuit supported by the first flexible substrate and electrically connected to the signal generator, and a fourth LC circuit supported by the second flexible substrate and electrically connected to the signal processor, the third LC circuit comprising a third inductor and a third capacitor, the fourth LC circuit comprising a fourth inductor and a fourth capacitor, and the third inductor being aligned with the fourth inductor.

11. A method for measuring an air gap between a first surface of a first part and a second surface of a second part, comprising:
adhering first flexible hybrid electronics comprising a first LC circuit formed on a first flexible substrate to the first surface of the first part;
adhering second flexible hybrid electronics comprising a second LC circuit formed on a second flexible substrate to the second surface of the second part;
driving a first inductor of the first LC circuit with a first alternating current to produce a changing magnetic flux that passes through a second inductor of the second LC circuit, which first alternating current has a frequency equal to a resonant frequency of the second LC circuit;
inducing a second alternating current in the second inductor due to the magnetic flux passing through the second inductor;
rectifying the second alternating current into a first direct current;
converting the first direct current into first digital gap sensor measurement data that varies in dependence on a first distance separating the first and second inductors;
transmitting the first digital gap sensor measurement data to a digital signal processor; and
computing a first air gap size based on the first digital gap sensor measurement data, wherein the computing is performed by the digital signal processor.

12. The method as recited in claim 11 , wherein the first flexible hybrid electronics further comprises a third LC circuit and the second flexible hybrid electronics further comprises a fourth LC circuit, the method further comprising:
driving a third inductor of the third LC circuit with a third alternating current to produce a changing magnetic flux that passes through a fourth inductor of the fourth LC circuit, which third alternating current has a frequency equal to a resonant frequency of the fourth LC circuit;
inducing a fourth alternating current in the fourth inductor due to the magnetic flux passing through the fourth inductor;
rectifying the fourth alternating current into a second direct current;
converting the second direct current into second digital gap sensor measurement data that varies in dependence on a second distance separating the third and fourth second inductors;
transmitting the second digital gap sensor measurement data to the digital signal processor; and
computing a second air gap size based on the second digital gap sensor measurement data.

13. The method as recited in claim 12 , wherein the first and second parts are structural components of an aircraft, further comprising:
fabricating a shim having a thickness which varies in accordance with an air gap profile that includes the first and second air gap sizes; and
placing the shim in the air gap between the between the first and second parts.

14. The method as recited in claim 11 , wherein the first part is a structural component of an aircraft and the second part is a planar reference.

15. The method as recited in claim 11 , wherein converting the first direct current into first digital gap sensor measurement data is performed by a signal processor and transmitting the first digital gap sensor measurement data is performed by a transmit antenna, the method further comprising wirelessly transferring electric power to the signal processor via the transmit antenna.

16. A method for determining an air gap profile between a first surface of a first part and a second surface of a second part, comprising:
adhering first first flexible hybrid electronics comprising a first multiplicity of inductors formed on a first flexible substrate to the first surface of the first part;
adhering second flexible hybrid electronics comprising a second multiplicity of inductors formed on a second flexible substrate to the second surface of the second part, the inductors of the second multiplicity of inductors being respectively aligned with the inductors of the first multiplicity of inductors;
driving the inductors of the first multiplicity of inductors in sequence with respective first alternating currents to produce a changing magnetic flux that passes through respective aligned inductors of the second multipli

Assignees

• Boeing Co

Inventors

• Rogers John E
• Smith Robert Alan

Classifications

• B64F5/00 Primary

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title

• G01B7/14 Primary

  for measuring distance or clearance between spaced objects or spaced apertures (G01B7/30 takes precedence) · CPC title

• G05B19/4099

  Surface or curve machining, making three-dimensional [3D] objects, e.g. desktop manufacturing · CPC title

• G05B19/40931

  concerning programming of geometry · CPC title

• G05B2219/35062

  Derive mating, complementary, mirror part from computer model data · CPC title