FIBER OPTIC SENSING AND CONTROL SYSTEM

• US 20170021914A1
• Filed: 12/08/2014
• Published: 01/26/2017
• Est. Priority Date: 12/11/2013
• Status: Abandoned Application

• Current Assignee: Moog Incorporated
• Original Assignee: Moog Incorporated
• Inventors: Small, George L., Lloyd, Glynn, Gitnes, Seth E.
• Application Number:
  US15/102,481
• Publication Number:
  US 20170021914A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: B64C 13/16 actuated automatically, e.g. responsive to gust detectors
• CPC Class Codes: B64C 13/503 Fly-by-Wire
• CPC Class Codes: B64D 2045/001 for indicating symmetry of flaps deflection
• CPC Class Codes: B64D 2045/0085 Devices for aircraft health monitoring, e.g. monitoring flutter or vibration
• CPC Class Codes: B64D 45/0005 Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear
• CPC Class Codes: G01D 5/353 influencing the transmission properties of an optical fibre
• CPC Class Codes: G01K 11/3206 at discrete locations in the fibre, e.g. using Bragg scattering
• CPC Class Codes: Y02T 50/40 Weight reduction

Abstract

An improved flight control system comprising a flight control surface of an aircraft or spacecraft, a first optical fiber having a fiber optic sensor configured to sense a first parameter associated with the flight control surface at a first position and a second fiber optic sensor configured to sense a second parameter associated with the flight control surface at a second location, an interrogator connected to the first optical fiber and configured to convert the sensed parameters from both the first fiber optic sensor and the second fiber optic sensor into an electrical signal, and the interrogator communicating with a flight control computer.

Claims

1. An aeronautical control system comprising:

a flight control surface of an aircraft or spacecraft;

a first optical fiber;

said first optical fiber having a fiber optic sensor configured and arranged to sense a first parameter associated with said flight control surface at a first position and a second fiber optic sensor configured and arranged to sense a second parameter associated with said flight control surface at a second location;

an interrogator connected to said first optical fiber and configured and arranged to convert said sensed parameters from both said first fiber optic sensor and said second fiber optic sensor into an electrical signal; and

said interrogator communicating with a flight control computer.

2. The control system set forth in claim 1, wherein said first parameter and said second parameter are the same parameter.

3. The control system set forth in claim 1, wherein said first parameter and said second parameter are different parameters.

4. The control system set forth in claim 1, wherein said first parameter and said second parameter are selected from a group consisting of position, load, skew, pressure, fluid level, temperature and strain.

5. The control system set forth in claim 1, wherein said first fiber optic sensor comprises a fiber Bragg grating.

6. The control system set forth in claim 1, wherein said first location and said second location are selected from a group consisting of a wing, a horizontal stabilizer, a vertical stabilizer, and a body or fuselage of an aircraft or spacecraft.

7. The control system set forth in claim 1, wherein said first location and said second location are selected from a group consisting of a aileron, an elevator, a rudder, a spoilers, a flap, a flaperon and a slat of an aircraft.

8. The control system set forth in claim 1, and further comprising a third fiber optic sensor configured and arranged to sense a third parameter associated with said flight control surface at a third position and a fourth fiber optic sensor configured and arranged to sense a fourth parameter associated with said flight control surface at a fourth position.

9. An aeronautical control system comprising:

a flight control surface of an aircraft or spacecraft;

an actuator configured and arranged to apply a force to said flight control surface;

a first optical fiber;

said first optical fiber having a fiber optic sensor configured and arranged to sense a first parameter associated with said flight control surface;

an interrogator connected to said first optical fiber and configured and arranged to convert said sensed parameters from said first fiber optic sensor into an electrical signal; and

said interrogator communicating with said actuator.

10. The control system set forth in claim 9, wherein said interrogator is configured and arranged to send a command sign to said actuator multiplexed over said first optical fiber.

11. The control system set forth in claim 9, wherein said first optical fiber has a second fiber optic sensor configured and arranged to sense a second parameter associated with said flight control surface at a second location and said interrogator is configured and arranged to convert said sensed parameters from said second fiber optic sensor into an electrical signal.