Aircraft laser collision detection system

Patent metadata

Field	Value
Publication number	US-11635523-B2
Application number	US-202016948715-A
Country	US
Kind code	B2
Filing date	Sep 29, 2020
Priority date	Sep 29, 2020
Publication date	Apr 25, 2023
Grant date	Apr 25, 2023

Abstract

Aircraft anti-collision systems, anti-collision methods, and aircraft with anti-collision systems and methods are provided. A method including transmitting, by a light emitter, a first light pulse proximate to a wing edge at a first time, detecting, by a light detector, a reflection of the first light pulse at a second time, determining, by a processor, a distance from a first object to the wing edge in response to the first time and the second time, calculating, by the processor, a possible contact occurrence in response to the distance and an aircraft velocity, and controlling a user interface with the processor to generate a user alert in response to the possible contact occurrence.

First claim

What is claimed is:

1. A collision detection system within an aircraft, the collision detection system comprising:
a first light emitter adapted to be mounted to the aircraft, the first light emitter being configured for transmitting a first light pulse at a first distance to a wing edge and providing a first time indicative of the transmitting of the first light pulse, the first light emitter having a fixed position such that the first light pulse is transmitted at an elevation and an azimuth parallel to the wing edge;
a first light detector, adapted to be mounted to the aircraft, the first light detector being configured to detect a reflection of the first light pulse and to provide a second time indicative of the detection of the reflection of the light pulse;
a processor adapted to be mounted to the aircraft and configured to receive the first time and the second time, to determine a possible contact occurrence between a first object and the wing edge based, at least in part, on the first time and the second time, and to generate a first control signal in response to determining the possible contact occurrence; and
a user interface, adapted to be mounted to the aircraft and configured to obtain the first control signal from the processor and to provide a user alert in response to the first control signal.

2. The collision detection system within the aircraft of claim 1 , further including an aircraft flight controller adapted to be mounted on the aircraft and configured to provide an aircraft velocity and wherein the processor is further configured to obtain the aircraft velocity from the flight controller and to determine the possible contact occurrence is determined, based, in part, on the aircraft velocity.

3. The collision detection system of claim 1 , wherein the first light pulse is transmitted parallel to a leading wing edge.

4. The collision detection system of claim 1 , wherein the first light pulse is transmitted in response to the aircraft taxiing.

5. The collision detection system within an aircraft of claim 1 further including a second light emitter, adapted to be mounted to the aircraft and configured to transmit a second light pulse at a second distance to the wing edge, the second light emitter having a fixed position such that the second light pulse is transmitted at the elevation and the azimuth parallel to the wing edge and parallel to the first light pulse, wherein the second distance is greater than the first distance and wherein the processor is further configured to detect a second object in response to the second light pulse, to determine that the second object is in a path of the wing edge and to generate a second control signal in response to the second object being within the path of the wing edge.

6. The collision detection system of claim 5 , wherein the first light pulse is transmitted along a leading edge of an aircraft wing and wherein the second light pulse is transmitted along a trailing edge of the aircraft wing.

7. The collision detection system of claim 1 , wherein the first control signal is generated in response to the first object being within a path of the wing edge.

8. The collision detection system of claim 1 , wherein the first light emitter and the first light detector are located on an aircraft fuselage and wherein the first light pulse is transmitted parallel to the wing edge.

9. The collision detection system of claim 1 , wherein the first light emitter is further configured to transmit a second light pulse at a second distance to the wing edge where the second distance is greater than the first distance and wherein the processor is further configured to detect a second object in response to the second light pulse and to generate a second control signal in response to the second object being within a path of the wing edge.

10. A method comprising:
transmitting, by a light emitter, a first light pulse proximate to a wing edge at a first time the light emitter having a fixed position such that the first light pulse is transmitted at an elevation and an azimuth parallel to the wing edge;
detecting, by a light detector, a reflection of the first light pulse at a second time;
determining, by a processor, a distance from a first object to the wing edge in response to the first time and the second time;
calculating, by the processor, a possible contact occurrence in response to the distance and an aircraft velocity; and
controlling a user interface with the processor to generate a user alert in response to the possible contact occurrence.

11. The method of claim 10 , wherein the aircraft velocity is determined in response to data provided by a global positioning system.

12. The method of claim 10 , wherein the wing edge is a leading wing edge and wherein the first light pulse is transmitted in response to the aircraft velocity being a forward velocity and not transmitted in response to the aircraft having a rearward velocity.

13. The method of claim 10 , wherein the wing edge is a trailing wing edge and wherein the first light pulse is transmitted in response to the aircraft velocity being a rearward velocity and not transmitted in response to the aircraft having a rearward velocity.

14. The method of claim 10 , wherein the first light pulse is transmitted parallel to the wing edge.

15. The method of claim 10 , wherein the first light pulse is transmitted in response to the aircraft taxiing.

16. The method of claim 10 , wherein the light emitter and the light detector are located on an aircraft fuselage and wherein the first light pulse is transmitted parallel to the wing edge.

17. The method of claim 10 , wherein the light emitter is further configured to transmit a second light pulse proximate to the wing edge wherein the processor is further configured to locate a second object and to generate the user alert in response to the second object being within a path of the wing edge.

18. The method of claim 10 , wherein the user alert is generated in response to the first object being within a path of the wing edge.

19. An anti-collision system for an aircraft, comprising:
a first light emitter, located on an aircraft fuselage, configured for transmitting a first light pulse at a first distance from a wing edge, the first light emitter having a first fixed position such that the first light pulse is transmitted at an elevation and an azimuth parallel to the wing edge;
a second light emitter, located on the aircraft fuselage, configured for transmitting a second light pulse at a second distance from the wing edge wherein the first distance is greater than the second distance the second light emitter having a second fixed position such that the second light pulse is transmitted at an elevation and an azimuth parallel to the wing edge and the first light pulse;
a detector for detecting a reflection of the first light pulse and a reflection of the second light pulse; and
a processor configured to generate a first user alert in response to a propagation time of the first light pulse being indicative of a detection of a first object at the first distance to the wing edge and being within a path of the wing edge, the processor being further configured to generate a second user alert in response to a propagation time of the second light pulse being indicative of a detection of the first object at the second distance to the wing edge and being within the path of the wing edge.

20. The anti-collision system for an aircraft of claim 19 wherein the first user alert is an optical alert

Assignees

• Gulfstream Aerospace Corp

Inventors

• Toler Brian

Classifications

• G08G5/723

  from the aircraft · CPC title

• G08G5/80

  Anti-collision systems · CPC title

• G08G5/51

  for control when on the ground, e.g. taxiing or rolling · CPC title

• G08G5/21

  located onboard the aircraft · CPC title

• G01S7/4811

  common to transmitter and receiver · CPC title