Window for an aircraft, aircraft, and method for determining the position at which a laser beam impacts a window

Patent metadata

Field	Value
Publication number	US-12504501-B2
Application number	US-202318387219-A
Country	US
Kind code	B2
Filing date	Nov 6, 2023
Priority date	Nov 8, 2022
Publication date	Dec 23, 2025
Grant date	Dec 23, 2025

Abstract

A window for an aircraft, the window including a first transparent layer, and a first plurality of light detectors arranged around a circumference of the first transparent layer to measure the intensity of light refracted upon entering and exiting the first transparent layer. An aircraft and a method for determining the point at which a laser beam impacts a window of the aircraft are disclosed.

First claim

The invention claimed is:

1 . A window for an aircraft, the window comprising:
a first transparent layer; a first plurality of light detectors arranged around a circumference of the first transparent layer, coplanar with the first transparent layer, and configured to measure an intensity of light refracted upon entering and exiting the first transparent layer; a second transparent layer; and a second plurality of light detectors arranged around a circumference of the second transparent layer, coplanar with the second transparent layer, and configured to measure an intensity of light refracted upon entering and exiting the second transparent layer.

2 . The window according to claim 1 , wherein the first plurality of light detectors are arranged to cover an entirety of the circumference of the first transparent layer in regular intervals.

3 . The window according to claim 2 , wherein the second plurality of light detectors are arranged to cover an entirety of the circumference of the second transparent layer in regular intervals.

4 . The window according to claim 1 , comprising a layer of dimmable electrochromic glass.

5 . The window according to claim 4 , wherein the layer of dimmable electrochromic glass comprises a plurality of individually dimmable subsegments.

6 . An aircraft comprising the window according to claim 1 , wherein the window comprises a windshield of a cockpit.

7 . The window according to claim 1 , wherein the first plurality of light detectors are configured to determine an average between a position at which a laser beam enters the first transparent layer and a position at which the laser beam exits the first transparent layer.

8 . The window according to claim 7 , wherein the second plurality of light detectors are configured to determine an average between a position at which a laser beam enters the second transparent layer and a position at which the laser beam exits the second transparent layer.

9 . The window according to claim 1 , wherein the second plurality of light detectors are configured to determine an average between a position at which a laser beam enters the second transparent layer and a position at which the laser beam exits the second transparent layer.

10 . The window according to claim 1 , wherein the second plurality of light detectors are arranged to cover an entirety of the circumference of the second transparent layer in regular intervals.

11 . A method for determining a position at which a laser beam impacts a window, the method comprising:
measuring an intensity of light refracted upon entering and exiting a first transparent layer of the window by a first plurality of light detectors arranged around a circumference of the first transparent layer, coplanar with the first transparent layer; measuring an intensity of light refracted upon entering and exiting a second transparent layer of the window by a second plurality of light detectors arranged around a circumference of the second transparent layer, coplanar with the second transparent layer; determining a position at which the laser beam entered the first transparent layer using the intensity of refracted light measured by each of the first plurality of light detectors; and determining a point of origin of the laser beam.

12 . The method according to claim 11 , comprising wherein determining the point of origin of the laser beam uses the position at which the laser beam entered the first transparent layer.

13 . The method according to claim 12 , comprising:
determining a position at which the laser beam entered the second transparent layer using the intensity of refracted light measured by each of the second plurality of light detectors; and determining an angle at which the laser beam impacted the window utilizing the position at which the laser beam entered the first transparent layer and the position at which the laser beam entered the second transparent layer; wherein the angle at which the laser beam impacted the window is used to determine the point of origin of the laser beam.

14 . The method according to claim 11 , wherein the window is part of a windshield of a cockpit of an aircraft, the window comprising:
the first transparent layer; and the first plurality of light detectors, which are arranged around the circumference of the first transparent layer and configured to measure the intensity of the light refracted upon entering and exiting the first transparent layer; and wherein at least one of altitude, roll, pitch, or yaw of the aircraft is used to determine the point of origin of the laser beam.

15 . The method according to claim 11 , wherein the laser beam impacts the window, the window comprising:
the first transparent layer; the first plurality of light detectors arranged around the circumference of the first transparent layer and configured to measure the intensity of the light refracted upon entering and exiting the first transparent layer; and a layer of dimmable electrochromic glass; the method comprising dimming the layer of dimmable electrochromic glass upon impact of the laser beam on the window.

16 . The method according to claim 15 , wherein:
the laser beam impacts the window; and the layer of dimmable electrochromic glass comprises a plurality of individually dimmable subsegments; and only individually dimmable subsegments of the plurality of individually dimmable subsegments that are impacted by the laser beam are dimmed.

17 . The method according to claim 11 , wherein the point of origin of the laser beam is determined utilizing data collected at least at two different points in time.

18 . The method according to claim 11 , wherein the first plurality of light detectors are configured to determine an average between a position at which a laser beam enters the first transparent layer and a position at which the laser beam exits the first transparent layer.

19 . The method according to claim 18 , wherein the second plurality of light detectors are configured to determine an average between a position at which a laser beam enters the second transparent layer and a position at which the laser beam exits the second transparent layer.

20 . The method according to claim 11 , wherein the second plurality of light detectors are configured to determine an average between a position at which a laser beam enters the second transparent layer and a position at which the laser beam exits the second transparent layer.

Assignees

• Airbus Operations Gmbh

Inventors

• Linde Peter
• Telkamp Michael

Classifications

• B64D45/00

  Aircraft indicators or protectors not otherwise provided for · CPC title

• B64C1/14

  Windows; Doors; Hatch covers or access panels; Surrounding frame structures; Canopies; Windscreens {accessories therefor, e.g. pressure sensors, water deflectors, hinges, seals, handles, latches, windscreen wipers}(fairings movable in conjunction with undercarriage elements B64C25/16; bomb doors B64D1/06) · CPC title

• B60J3/04

  adjustable in transparency · CPC title

• B64C1/1484

  Windows (B64C1/1492 takes precedence) · CPC title

• G01S5/16 Primary

  using electromagnetic waves other than radio waves · CPC title