Indicators for use in oxygen systems

Patent metadata

Field	Value
Publication number	US-12533536-B2
Application number	US-202217719103-A
Country	US
Kind code	B2
Filing date	Apr 12, 2022
Priority date	Dec 20, 2021
Publication date	Jan 27, 2026
Grant date	Jan 27, 2026

Abstract

An oxygen system for an aircraft may have a chemical oxygen generator; an oxygen mask; and a tube assembly extending from the chemical oxygen generator to the oxygen mask. The tube assembly may have a first tube and a second tube. The first tube defines a fluid conduit that fluidly couples the chemical oxygen generator to the oxygen mask in response to being in use. The second tube may be configured to house a plurality of lights therein.

First claim

What is claimed is:

1 . An oxygen system for an aircraft, the oxygen system comprising:
a chemical oxygen generator; an oxygen mask; and a tube assembly comprising a first tube and a second tube, each of the first tube and the second tube extending from the chemical oxygen generator to the oxygen mask, the first tube defining a fluid conduit that fluidly couples the chemical oxygen generator to the oxygen mask in response to being in use, the second tube configured to house a plurality of lights therein, wherein the first tube and the second tube define a chamber radially therebetween, and wherein the plurality of lights are disposed within the chamber, wherein the first tube comprising an outer circumferential surface and the second tube comprising an inner circumferential surface, the chamber is positioned between the outer circumferential surface of the first tube and the inner circumferential surface of the second tube, and wherein at a section of the tube assembly, and the chamber extend around the entire outer circumferential surface of the first tube to surround the first tube at the section of the tube assembly.

2 . The oxygen system of claim 1 , wherein further comprising the plurality of lights extends along a majority of a longitudinal length of the tube assembly.

3 . The oxygen system of claim 2 , wherein the plurality of lights comprise a first set of lights and a second set of lights.

4 . The oxygen system of claim 3 , wherein the first set of lights are configured to emit a first color, and wherein the second set of lights are configured to emit a second color that is different than the first color.

5 . The oxygen system of claim 2 , further comprising a controller in electrical communication with the plurality of lights.

6 . The oxygen system of claim 5 , wherein the controller is configured to command the plurality of lights to emit a first color in response to determining the oxygen mask is operable and not in use, and wherein the controller is configured to command the plurality of lights to emit a second color in response to determining the oxygen mask is inoperable.

7 . The oxygen system of claim 6 , wherein the controller is configured to command the plurality of lights to emit a third color in response to determining the oxygen mask is in use and operable.

8 . The oxygen system of claim 1 , the chamber is recessed from an outer diameter of the tube assembly.

9 . An oxygen system for an aircraft, comprising:
an oxygen mask; a tube assembly comprising a first tube and a second tube, the first tube defining a fluid conduit configured to transfer a fluid to the oxygen mask, the first tube and the second tube defining a chamber therebetween; and a plurality of lights disposed in the chamber and extending along a majority of a longitudinal length of the tube assembly, wherein the first tube comprising an outer circumferential surface and the second tube comprising an inner circumferential surface, the chamber is positioned between the outer circumferential surface of the first tube and the inner circumferential surface of the second tube, and wherein at a section of the tube assembly, and the chamber extend around the entire outer circumferential surface of the first tube to surround the first tube at the section of the tube assembly.

10 . The oxygen system of claim 9 , further comprising a controller in electrical communication with the plurality of lights, the controller configured to electrically couple a first light in the plurality of lights to a power source in order to emit a first color in response to determining the oxygen mask is not in use and operable, the controller further configured to command a second light in the plurality of lights to the power source to emit a second color in response to determining the oxygen mask is inoperable.

11 . The oxygen system of claim 10 , wherein the controller is further configured to electrically couple a third light in the plurality of lights to the power source to emit a third color in response to determining the oxygen mask is in use and operable.

12 . The oxygen system of claim 10 , wherein the first color is different from the second color.

13 . The oxygen system of claim 9 , wherein the oxygen system further comprises a chemical oxygen generator configured to be fluidly coupled to the oxygen mask via the fluid conduit during use of the oxygen system.

14 . The oxygen system of claim 9 , wherein the plurality of lights are spaced apart longitudinally along a length of the tube assembly.

15 . A passenger service unit in the aircraft, comprising the oxygen system of claim 9 .

16 . An aircraft, comprising the oxygen system of claim 9 .

17 . A method, comprising:
determining, via a processor, a status of an oxygen mask in an oxygen system; and commanding, via the processor, the oxygen system to emit a color from a plurality of lights extending along a majority of a longitudinal length of a tube assembly in the oxygen system in response to determining the status of the oxygen mask, wherein the tube assembly comprising a first tube and a second tube, the first tube and the second tube define a chamber radially therebetween, and wherein the plurality of lights are disposed within the chamber, wherein the first tube comprising an outer circumferential surface and the second tube comprising an inner circumferential surface, the chamber is positioned between the outer circumferential surface of the first tube and the inner circumferential surface of the second tube, and wherein at a section of the tube assembly, the chamber extend around the entire outer circumferential surface of the first tube to surround the first tube at the section of the tube assembly.

18 . The method of claim 17 , wherein the color is a first color in response to the status being operable and not in use, and wherein the color is a second color in response to the status being inoperable.

19 . The method of claim 18 , wherein the first color is different from the second color.

20 . The method of claim 19 , wherein the color is a third color in response to the status being operable and in use, the third color being different from the first color and the second color.

Assignees

• Be Aerospace Inc

Inventors

• Puttaswamaiah Bhaskara Chikkanayakanahalli
• Raj Mayank

Classifications

• B64D2231/025

  Oxygen masks; Mask storages; Features related to mask deployment · CPC title

• B64D2045/007

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

• A62B7/14

  for high-altitude aircraft · CPC title

• G08B5/36

  using visible light sources · CPC title

• F21V33/0076

  Safety or security signalisation, e.g. smoke or burglar alarms, earthquake detectors; Self-defence devices · CPC title