Laser rangefinder systems with divergent lenses for aircraft wingtip collision avoidance systems

Patent metadata

Field	Value
Publication number	US-11774597-B2
Application number	US-202017247763-A
Country	US
Kind code	B2
Filing date	Dec 22, 2020
Priority date	Dec 22, 2020
Publication date	Oct 3, 2023
Grant date	Oct 3, 2023

Abstract

An aircraft includes a fuselage, a main wing coupled with and extending outward from the fuselage, and a collision avoidance system coupled with the fuselage adjacent the main wing. The collision avoidance system includes first and second laser rangefinders and a detection circuit. The first and second laser rangefinders are configured to generate laser beams laterally outward of the fuselage and include diverging lenses spreading the laser beams in a vertical dimension. The detection circuit is coupled with the first laser rangefinder and the second laser rangefinder to: detect an object within a collision risk zone adjacent to the main wing based on input from at least one of the first laser rangefinder and the second laser rangefinder; and generate an alert that the object is at risk of colliding with the main wing.

First claim

What is claimed is:

1. An aircraft, comprising:
a fuselage;
a flight deck;
a main wing coupled with and extending outward from the fuselage; and
a collision avoidance system coupled with the fuselage adjacent the main wing, the collision avoidance system comprising:
a first laser rangefinder configured to generate a first laser beam in a first direction laterally outward of the fuselage;
a second laser rangefinder configured to generate a second laser beam in a second direction laterally outward and farther away from the main wing relative to the first direction;
a first diverging lens optically coupled with the first laser rangefinder to spread the first laser beam in a vertical dimension;

a second diverging lens optically coupled with the second laser rangefinder to spread the second laser beam in a vertical dimension, wherein beam spreading characteristics of the first diverging lens are different than beam spreading characteristics of the second diverging lens to account for the first and second directions, and wherein the second diverging lens spreads the second laser beam less as the second angle departs from perpendicular to a longitudinal axis of the aircraft; and
a detection circuit coupled with the first laser rangefinder and the second laser rangefinder to:
detect an object within a collision risk zone adjacent to the main wing based on input from at least one of the first laser rangefinder and the second laser rangefinder; and
generate an alert that the object is at risk of colliding with the main wing.

2. The aircraft of claim 1 , wherein the main wing includes a winglet having a winglet height in the vertical dimension, and wherein the first diverging lens has a shape that spreads the first laser beam to be taller than the winglet height in the vertical dimension at the winglet.

3. The aircraft of claim 2 , wherein the shape of the first diverging lens does not spread the first laser beam in a horizontal direction.

4. The aircraft of claim 2 , wherein the first laser rangefinder and the second laser rangefinder are oriented such that a bottom edge of the first laser beam and the second laser beam are proximate to the winglet.

5. The aircraft of claim 2 , wherein the detection circuit is configured to detect the object by disregarding measurements from the first laser rangefinder and the second laser rangefinder that are beyond a threshold determined based on a lateral distance to the winglet and a vertical distance that is based on a vertical spread of the first laser beam and the second laser beam.

6. The aircraft of claim 1 , wherein the collision avoidance system further comprises a rangefinder housing, and wherein the first laser rangefinder and the second laser rangefinder are disposed in the rangefinder housing.

7. The aircraft of claim 6 , wherein the rangefinder housing is disposed in the fuselage forward of the main wing and is oriented forward to detect objects that are a collision risk when the aircraft is moving forward.

8. The aircraft of claim 6 , wherein the rangefinder housing is disposed in the fuselage aft of the main wing and is oriented backward to detect objects that are a collision risk when the aircraft is moving backward.

9. The aircraft of claim 1 , wherein the detection circuit is configured to:
generate the alert as a caution when the object is close to but is not in a path of the main wing; and
generate the alert as a warning when the object is in the path of the main wing.

10. The aircraft of claim 1 , further comprising a display operationally coupled with the detection circuit, the display configured to indicate the alert as a top view of the aircraft with an indicator at a detected position of the object.

11. The aircraft of claim 10 , wherein the display is a portable computing device for use by at least one of a pilot and a tug driver and the display is configured to color-code the alert based on whether the object is in a path of the main wing.

12. A collision avoidance system for an aircraft having a fuselage and a main wing coupled with and extending outward from the fuselage, the collision avoidance system comprising:
a rangefinder housing configured to be coupled with the fuselage and including a transparent wall shaped to form an outer mold line of the aircraft at the fuselage;
a first laser rangefinder configured to generate a first laser beam in a first direction laterally outward of the fuselage;
a second laser rangefinder configured to generate a second laser beam in a second direction laterally outward and farther away from the main wing relative to the first direction;
at least one diverging lens optically coupled with the first laser rangefinder and the second laser rangefinder to spread the first laser beam and the second laser beam in a vertical dimension; and
a detection circuit coupled with the first laser rangefinder and the second laser rangefinder to:
determine a path of the main wing by calculating a wing growth of the main wing based on a steering angle and a pivot axis of the aircraft;
generate at least one threshold based on a lateral distance to a wingtip of the main wing, the determined path of the main wing, and the calculated wing growth;
detect an object within a collision risk zone adjacent to the main wing based on input from at least one of the first laser rangefinder and the second laser rangefinder, wherein the collision risk zone is associated with the generated at least one threshold; and
generate an alert that the object is at risk of colliding with the main wing.

13. The collision avoidance system of claim 12 , wherein the first laser rangefinder and the second laser rangefinder are oriented in the rangefinder housing and cooperate with the at least one diverging lens to spread the first laser beam and the second laser beam to have a vertical height that is larger than a winglet height of a winglet at the wingtip of the aircraft when the rangefinder housing is installed on the aircraft.

14. The collision avoidance system of claim 13 , wherein the first laser rangefinder and the second laser rangefinder cooperate with the rangefinder housing to be oriented, when installed on the aircraft, such that a bottom edge of the first laser beam and the second laser beam are proximate to the wingtip.

15. The collision avoidance system of claim 13 , wherein the detection circuit is configured to detect the object by disregarding measurements from the first laser rangefinder and the second laser rangefinder that are beyond a caution threshold determined based on a lateral distance to the winglet and a vertical distance that is based on a vertical spread of the first laser beam and the second laser beam.

16. The collision avoidance system of claim 12 , wherein the detection circuit is configured to:
generate the alert as a caution when the object is close to but is not in a path of the main wing; and
generate the alert as a warning when the object is in the path of the main wing.

17. The collision avoidance system of claim 12 , further comprising a display operationally coupled with the detection circuit, the display configured to indicate the alert as a top view of the aircraft with an indicator at a detected position of the object.

18. A collision avoidance system for an aircraft having a fuselage and a main wing coupled with and extending outward from the fuselage and terminating at a wingtip, the collision avoidance system comprising:
a plurality of laser rangefinders, each configured to generate a respective laser beam in the non-visual spectrum, wherein t

Assignees

• Gulfstream Aerospace Corp

Inventors

• Jordan Jim
• Bohanan Scott
• Hausmann Jeffrey

Classifications

• 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

• G01S17/933 Primary

  of aircraft or spacecraft · CPC title

• B64D43/00

  Arrangements or adaptations of instruments · CPC title