Remote optical control surface indication system

• US 10,435,173 B2
• Filed: 01/16/2017
• Issued: 10/08/2019
• Est. Priority Date: 01/16/2017
• Status: Active Grant

• Current Assignee: The Boeing Co.
• Original Assignee: The Boeing Co.
• Inventors: Konyndyk, David M., James, Jerry A.
• Primary Examiner(s): Pontius, James M
• Application Number:
  US15/407,076
• Publication Number:
  US 20180201390A1
• Time in Patent Office: 995 Days
• Field of Search: None
• CPC Class Codes: B64C 13/02 Initiating means
• 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: B64F 5/60 Testing or inspecting aircraft components or systems
• CPC Class Codes: B64U 20/87 Mounting of imaging devices, e.g. mounting of gimbals
• CPC Class Codes: H04N 23/20 for generating image signals from infrared radiation only
• CPC Class Codes: H04N 23/51 Housings
• CPC Class Codes: H04N 23/56 provided with illuminating means
• CPC Class Codes: H04N 5/33 Transforming infrared radiation cameras or camera modules for generating image signals from infrared radiation H04N23/20; circuitry of SSIS for transforming infrared radiation into image signals H04N25/20

Abstract

A remote optical control surface indication system comprising mechanisms configured to engage heads of respective fasteners that attach an alignment indexing plate to a vehicular structure having a control surface coupled thereto. The system further comprises: a camera having a field of view that encompasses a portion of an end face of the control surface when the mechanisms are engaged with the fasteners and when the control surface is in a neutral position; a source of light that is activatable to project light that illuminates the end face of the control surface; a display screen comprising an array of pixels; and a computing system configured to process image data captured by the camera to determine a current position of a centerline of the end face of the control surface relative to a baseline position and control the display screen to display symbology indicating the current position relative to the baseline position.

Claims

1. An optical control surface indication system comprising:

a base assembly comprising a base plate and first and second mechanisms configured to respectively engage first and second features on a vehicular structure having a control surface movably coupled thereto;

a camera having a field of view that encompasses a portion of an end face of the control surface when the first and second mechanisms are engaged with the first and second features and when the control surface is in a neutral position;

a source of light that is activatable to project light that illuminates the portion of the end face of the control surface;

a first display screen comprising an array of pixels; and

a first computing system configured to perform the following operations;

processing image data captured by the camera to determine a current position of the control surface relative to a neutral position of the control surface; and

controlling the first display screen to display symbology indicating the current position of the control surface relative to its neutral position.

2. The optical control surface indication system as recited in claim 1, wherein the vehicular structure is an aircraft fuselage, the first and second features are respective heads of fasteners which attach an indexing plate to the fuselage, the control surface is a rudder, and the end face is a trailing edge.

3. The optical control surface indication system as recited in claim 1, wherein the source of light comprises a multiplicity of infrared light-emitting diodes and the camera is an infrared camera.

4. The optical control surface indication system as recited in claim 1, wherein the symbology comprises a graphical representation of an aircraft butt line marking corresponding to a baseline position of a centerline of the end face when the control surface is in its neutral position and a movable indicator separated from the graphical representation of the aircraft butt line marking by a distance proportional to the distance separating the current position of the centerline from its baseline position.

5. The optical control surface indication system as recited in claim 1, wherein the first computing system processes the image data by detecting first and second edges of the end face of the control surface, and calculating first and second positions of the first and second edges respectively, the current position of a centerline being midway between the first and second positions.

6. The optical control surface indication system as recited in claim 1, wherein the symbology comprises a plurality of alphanumeric characters representing an offset of the current position of a centerline of the end face of the control surface relative to a baseline position of the centerline corresponding to the neutral position of the control surface.

7. The optical control surface indication system as recited in claim 1, wherein the first and second mechanisms comprise respective spring-loaded plunger cups.

8. The optical control surface indication system as recited in claim 1, wherein the base assembly further comprises a support member attached to the base plate and a magnet attached to the support member, the first mechanism being movably coupled to the support member, and wherein the system further comprises a mounting plate made of ferromagnetic material, a suction cup attached to the mounting plate, and a lanyard having one end coupled to the mounting plate and another end coupled to the base plate.

9. The optical control surface indication system as recited in claim 1, wherein the first computing system is further configured to adapt the processing of image data to lighting conditions.

10. The optical control surface indication system as recited in claim 1, further comprising an optical target mounted to the control surface, the optical target comprising a reflector.

11. The optical control surface indication system as recited in claim 10, wherein the optical target further comprises a pair of wings made of opaque material disposed on opposite sides of the reflector.

12. The optical control surface indication system as recited in claim 1, further comprising a first transceiver and a first wireless communication interface that allows the first computing system to communicate with the first transceiver, the system further comprising a handheld unit comprising a second computing system, a second transceiver, a second wireless communication interface that allows the second computing system to communicate with the second transceiver, and a second display screen comprising an array of pixels, wherein the second computing system is configured to control the second display screen to display symbology indicating the current position of the control surface relative to the neutral position of the control surface based on information received by the second transceiver from the first transceiver.