Systems and methods for integrated, multi-functional, fault tolerant sensing and communication

Patent metadata

Field	Value
Publication number	US-10337935-B2
Application number	US-201715835814-A
Country	US
Kind code	B2
Filing date	Dec 8, 2017
Priority date	Dec 12, 2016
Publication date	Jul 2, 2019
Grant date	Jul 2, 2019

Abstract

A fiber-optic sensor system includes a structure having a fiber-optic cable operatively connected thereto. The system includes a network controller with an interrogator operatively connected to the fiber-optic cable to receive optical energy indicative of a characteristic of the structure therefrom and convert optical energy to electrical energy and electrical energy to optical energy for data communication. A sensor and/or a data source are operatively connected to the fiber-optic cable through the network controller to transmit data through the fiber-optic cable and receive data therefrom.

First claim

What is claimed is:

1. A fiber-optic sensor system comprising: a structure having a fiber-optic cable operatively connected thereto; a network controller having an interrogator operatively connected to the fiber-optic cable to receive optical energy indicative of a characteristic of the structure therefrom and convert optical energy to electrical energy and electrical energy to optical energy for data communication; and at least one of a data source or a sensor operatively connected to the fiber-optic cable through the network controller to transmit data through the fiber-optic cable and receive data therefrom; wherein the data source is at least one of an avionics system or a flight control system to provide data through the fiber optic cable to the network controller and to receive data through the fiber optic cable from the network controller; and, wherein the avionics system includes a health monitoring system and a rotor state feedback system operatively connected to the fiber-optic cable through the network controller to transmit data to the network controller and through the fiber-optic cable and to receive data therefrom.

2. The system as recited in claim 1 , wherein the fiber-optic cable is embedded within the structure.

3. The system as recited in claim 1 , wherein the structure is one of a plurality of structures wherein the fiber-optic cable extends between adjacent structures.

4. The system as recited in claim 1 , wherein the structure includes at least one of an access point to provide physical access to the fiber-optic cable within the structure, or a port to provide connection access to the fiber-optic cable and the network controller.

5. The system as recited in claim 1 , further comprising a sensing element inserted within the fiber-optic cable to modify optical energy in a way that is indicative of a characteristic of the structure and transmit the modified optical energy to the network controller.

6. The system as recited in claim 1 , wherein the network controller includes at least one optical component selected from a group consisting of an amplifier, a connector, a switch, a receiver, a laser diode, a photodiode and a transmitter.

7. A method for integrally sensing and communicating through a structure, comprising: transmitting optical energy indicative of a characteristic of a structure through a fiber-optic cable to an interrogator in a network controller; and transmitting data from at least one of a sensor or a data source from the network controller through the fiber-optic cable; wherein the data source is at least one of an avionics system or a flight control system to provide data through the fiber optic cable to the network controller and to receive data through the fiber optic cable from the network controller; and, wherein the avionics system includes a health monitoring system and a rotor state feedback system operatively connected to the fiber-optic cable through the network controller to transmit data to the network controller and through the fiber-optic cable and to receive data therefrom.

8. The method as recited in claim 7 , further comprising detecting damage in the fiber-optic cable with a health monitoring system operatively connected to the network controller.

9. The method as recited in claim 8 , wherein the fiber-optic cable is part of a fiber-optic network, the method further comprising mitigating faults within the fiber-optic network with the network controller by adjusting the configuration of the fiber-optic network to achieve fault tolerance.

10. The method as recited in claim 9 , wherein adjusting the configuration of the fiber-optic network includes using at least one of an optical switch or the network controller to reconfigure the transmitting of optical energy from the fiber-optic cable to a second fiber-optic cable within the fiber-optic cable network.

11. The method as recited in claim 7 , further comprising converting electrical energy to optical energy and vice versa.

12. The method as recited in claim 7 , wherein transmitting data from the data source includes transmitting avionics data through the fiber-optic cable to the network controller from an avionics system.

13. The method as recited in claim 12 , wherein transmitting data from the data source includes transmitting data through the fiber-optic cable from the network controller to the avionics system.

14. An aircraft comprising: a structure; a fiber-optic cable operatively connected to the structure; a network controller having an interrogator operatively connected to the fiber-optic cable to receive optical energy indicative of a characteristic of the structure therefrom; and at least one of a data source or a sensor operatively connected to the fiber-optic cable through the network controller to transmit data through the fiber-optic cable and receive data therefrom; wherein the data source is an avionics system to provide avionics data through the fiber-optic cable to the network controller and to receive data through the fiber-optic cable from the network controller; and, wherein the avionics system includes a structural health monitoring system and a rotor state feedback system operatively connected to the fiber-optic cable through the network controller to transmit data to the network controller and through the fiber-optic cable and to receive data therefrom.

15. The aircraft as recited in claim 14 , wherein the fiber-optic cable is embedded within the structure.

Assignees

• Sikorsky Aircraft Corp

Inventors

• Geiger Derek
• Cappelli Marcus D
• Garhart Jonathan K
• Sarlashkar Avinash
• Brookhart Andrew
• Davis Mark W

Classifications

• B64D2045/0085

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

• G01M5/0091

  by using electromagnetic excitation or detection · CPC title

• G01M5/0033

  by determining damage, crack or wear · CPC title

• G01M5/0016 Primary

  of aircraft wings or blades · CPC title

• G01M11/083

  by using an optical fiber in contact with the device under test [DUT] · CPC title