Optical indicator of mechanical state

Patent metadata

Field	Value
Publication number	US-10746378-B2
Application number	US-201715717412-A
Country	US
Kind code	B2
Filing date	Sep 27, 2017
Priority date	Oct 27, 2016
Publication date	Aug 18, 2020
Grant date	Aug 18, 2020

Abstract

A mechanical state indicator system concealed within an enclosure includes a light source for providing light and multiple light paths coupled to the light source for directing the light. Each of the light paths includes a gap configured to receive a mechanical state indicator rigidly coupled to a mechanism. Movement of the mechanism between a first state and a second state moves the mechanical state indicator into and out of the gap. Readouts are coupled to each of the light paths for displaying an indication of mechanical state based on a position of a respective mechanical state indicator. The readouts are co-located for collective viewing.

First claim

We claim:

1. An optical indicator system for an aircraft door, comprising:
a locking mechanism pivotable between a first position for locking the aircraft door and a second position for unlocking the aircraft door;
a fiber optic path optically coupling a light source to an indicator, such that light from the light source is transmitted through the fiber optic path to illuminate the indicator;
an intervening member rigidly coupled to the locking mechanism such that pivoting of the mechanism from the first position to the second position pivots the intervening member; and
a gap within the fiber optic path for receiving the intervening member such that light travels unencumbered across the gap when the intervening member is positioned outside the gap, and light is altered when the intervening member is pivoted into the gap.

2. The optical indicator system of claim 1 , wherein the intervening member comprises a filter for filtering light from the light source when the intervening member is positioned within the gap.

3. The optical indicator system of claim 1 , wherein the indicator is configured to receive light from a plurality of fiber optic paths, each configured for indicating position of a respective one of a plurality of intervening members, each rigidly coupled to a respective one of a plurality of locking mechanisms.

4. The optical indicator system of claim 3 , wherein the plurality of mechanisms are concealed within the aircraft door and spaced apart by a distance that prevents direct visual inspection from a single vantage point.

5. A mechanical state indicator system, comprising:
a light source for providing light, wherein the light source comprises 1) an electrically-powered light for nominally providing artificial light and 2) exposure to natural light for providing a backup source of light;
a plurality of fiber optic light paths coupled to the light source for directing the light, wherein each of the plurality of fiber optic light paths comprises a gap configured to receive a mechanical state indicator rigidly coupled to a mechanism, such that movement of the mechanism between a first state and a second state pivots the mechanical state indicator into and out of the gap, respectively; and
a plurality of readouts co-located into a single display, each of the plurality of readouts being respectively coupled to the plurality of fiber optic light paths for displaying an indication of mechanical state based on a gap position of a respective mechanical state indicator.

6. The mechanical state indicator system of claim 5 , wherein each of the plurality of fiber optic light paths comprise a first optical fiber separated by a predetermined distance from a second optical fiber to form the gap.

7. The mechanical state indicator system of claim 6 , wherein the first optical fiber emits light and the second optical fiber is aligned to receive the light.

8. The mechanical state indicator system of claim 5 , wherein the mechanical state indicator comprises a filter for filtering light through the gap such that the color of light received at a respective one of the plurality of readouts changes upon transition from the first state to the second state.

9. The mechanical state indicator system of claim 5 , wherein the mechanical state indicator comprises an opaque material for blocking light through the gap such that illumination of a respective one of the plurality of readouts ceases upon transition from the first state to the second state.

10. A system for enabling visual inspection of a plurality of locking mechanisms concealed inside an enclosed aircraft door, comprising:
a light source;
an optical display illuminated via light received from the light source, the optical display comprising a plurality of co-located readouts each corresponding to a respective one of the plurality of locking mechanisms;
a plurality of optical paths each optically coupling the light source with a respective one of the plurality of co-located readouts, each of the optical paths comprising:
a first optical-fiber cable having a first end and a second end, the first end being coupled to the light source, and the second end configured to emit light from the light source;
a second optical-fiber cable having a first end and a second end, the first end being aligned to receive light from the first optical-fiber cable, and the second end being coupled to the optical display;
a gap having a predetermined distance between the second end of the first optical-fiber cable and the first end of the second optical-fiber cable; and
an optical indicator mechanically coupled to a respective one of the plurality of locking mechanisms and configured to occupy the respective gap when the respective locking mechanism is in a first position, and to recede from the gap when the respective locking mechanism is in a second position, such that the optical indicator alters light from the light source to the optical display when the respective locking mechanism is in the first position.

11. The system of claim 10 , wherein the first position is a locked position and the second position is an unlocked position of the respective locking mechanism.

12. The system of claim 10 , wherein the optical indicator comprises a filter for filtering light from the light source to the optical display corresponding to the first position of the respective locking mechanism.

13. The system of claim 12 , wherein the filter is selected from the group consisting of a low-pass filter, a high-pass filter, and a bandpass filter.

14. The system of claim 10 , wherein the light source provides white light.

15. The system of claim 12 , wherein the filter is a color filter.

16. The system of claim 10 , wherein each locking mechanism comprises a plurality of positions and the optical indicator comprises a corresponding plurality of filters to occupy the gap when the locking mechanism is in one of the plurality of positions, respectively, to indicate a plurality of respective mechanical states by a plurality of respective colors.

17. The system of claim 10 , wherein the optical indicator is configured to block light from the light source when occupying the gap such that the optical display fails to illuminate when the locking mechanism is in the first position.

Assignees

• Textron Aviation Inc
• Textron Innovations Inc

Inventors

• Bachman Timothy James
• Smarsh Joseph Allan

Classifications

• E05B17/10 Primary

  Illuminating devices on or for locks or keys; {Transparent or translucent lock parts; Indicator lights} · CPC title

• B64D2045/007

  Indicators or signs in the cabin, e.g. exit signs or seat numbering · CPC title

• B64C1/1423

  Passenger doors · CPC title

• B64C1/1461

  Structures of doors or surrounding frames · CPC title

• B64D45/0005

  Devices specially adapted to indicate the position of a movable element of the aircraft, e.g. landing gear · CPC title