Fiber optic slat flap system and control lever

Patent metadata

Field	Value
Publication number	US-12351295-B2
Application number	US-202217990977-A
Country	US
Kind code	B2
Filing date	Nov 21, 2022
Priority date	Nov 21, 2022
Publication date	Jul 8, 2025
Grant date	Jul 8, 2025

Abstract

A control system performs a method of controlling a wing of an airplane. The control system includes an optical fiber, a bending device and a processor. The optical fiber is configured to receive light having an input optical phase. The bending device applies an external force on the optical fiber. The external force causes the light exiting the optical fiber to have an output optical phase. a processor determines a phase shift between the input optical phase and the output optical phase and controls the wing based on the phase shift.

First claim

What is claimed is:

1. A method of controlling a wing of an airplane, comprising:
passing a light through a modulation zone of an optical fiber, the modulation zone suspended between an entrance and an exit of a pressure modulation block, wherein the light has an input optical phase at the entrance of the pressure modulation block and an output optical phase at the exit of the pressure modulation block;
rotating a cam about a rotational axis to apply an external force to the optical fiber, the cam including a cam surface in contact with the optical fiber in the modulation zone for applying the external force, wherein rotating the cam about the rotational axis changes the external force on the optical fiber, thereby changing a bend of the optical fiber in the modulation zone and thus changing an output optical phase of the light at the exit;
determining a phase shift between the input optical phase and the output optical phase; and
controlling the wing of the airplane based on the phase shift.

2. The method of claim 1 , wherein controlling the wing further comprises adjusting one of a slat and a flap of the wing to a position corresponding to the phase shift.

3. The method of claim 1 , wherein a magnitude of the external force is related to a radius of the cam at a circumferential location of the cam surface that is in contact with the optical fiber.

4. The method of claim 1 , further comprising rotating the cam using a lever.

5. The method of claim 1 , wherein controlling the wing further comprises sending a command signal to the wing, wherein the command signal is an optical signal.

6. A control system for a wing of an airplane, comprising:
an optical fiber including a modulation zone suspended between an entrance and an exit of a pressure modulation block, wherein the optical fiber is configured to receive light having an input optical phase at the entrance and output a light having an output optical phase at the exit;
a bending device that applies an external force on the optical fiber, the bending device including a cam rotatable about a rotational axis and having a cam surface in contact with the optical fiber in the modulation zone for applying the external force, wherein rotating the cam about the rotational axis changes the external force on the optical fiber, thereby changing a bend of the optical fiber in the modulation zone and thus changing an output optical phase of the light at the exit; and
a processor configured to determine a phase shift between the input optical phase and the output optical phase and control the wing based on the phase shift.

7. The control system of claim 6 , wherein the processor is configured to control the wing by adjusting one of a slat and a flap to a position based on by the phase shift.

8. The control system of claim 6 , wherein a magnitude of the external force is related to a radius of the cam at a circumferential location of the cam surface that is in contact with the optical fiber.

9. The control system of claim 6 , further comprising a lever for rotating the cam.

10. The control system of claim 6 , wherein a detent position of the cam corresponds to a selected phase shift of the light in the optical fiber.

11. The control system of claim 6 , wherein the processor is further configured to send a command signal to the wing, wherein the command signal is an optical signal.

Assignees

• Hamilton Sundstrand Corp

Inventors

• Ankney Darrell E

Classifications

• G02F1/0134

  in optical waveguides · CPC title

• B64C13/503 Primary

  Fly-by-Wire · CPC title

• G02B2006/12138

  Sensor · CPC title

• B64C13/16

  actuated automatically, e.g. responsive to gust detectors · CPC title

• B64C13/0425 Primary

  for actuating trailing or leading edge flaps, air brakes or spoilers · CPC title