Aircraft landing gear monitoring and alerting system and method

Patent metadata

Field	Value
Publication number	US-11919657-B2
Application number	US-202016867985-A
Country	US
Kind code	B2
Filing date	May 6, 2020
Priority date	May 6, 2020
Publication date	Mar 5, 2024
Grant date	Mar 5, 2024

Abstract

A landing gear monitoring and alerting system includes a locking pin configured to be inserted into an aperture extending through a linkage of an extended landing gear assembly. When inserted into the aperture, the locking pin inhibits movement of the linkage to establish a locked state of the extended landing gear assembly. This system further includes a magnetic sensor and a communication module. The magnetic sensor is disposed proximate the aperture and is configured to sense a magnetic response indicative of the locking pin being disposed within the aperture. The magnetic sensor is configured to generate a sensor output indicative of the locking pin being disposed within the aperture. The communication module has a transmitter coupled to the magnetic sensor so as to receive the sensor output and is configured to responsively transmit a signal indicative of the locking pin being disposed within the aperture.

First claim

What is claimed is:

1. A landing gear monitoring and alerting system for an aircraft, the landing gear monitoring and alerting system comprising:
a locking pin configured to be inserted into an aperture extending through at least one linkage of an extended landing gear assembly, which when inserted inhibits movement of the at least one linkage to establish a locked state of the extended landing gear assembly;
a locking hook and a locking actuating rod coupled to the locking hook and the at least one linkage, wherein actuation of the locking actuating rod drives movement of the locking hook to hook around the locking pin to lock the locking pin in the aperture which inhibits movement of the at least one linkage and locks the extended landing gear assembly in the locked state;
a magnetic sensor disposed proximate the aperture and configured to sense a magnetic response, prior to take-off of the aircraft, indicative of the locking pin being disposed within the aperture to establish the locked state of the extended landing gear assembly, and the magnetic sensor being configured to generate a sensor output indicative of the locking pin being disposed within the aperture; and
a communication module having a transmitter being coupled to the magnetic sensor so as to receive the sensor output, prior to take-off of the aircraft, indicative of the locking pin being disposed within the aperture, and the communication module being configured to responsively transmit a signal, prior to take-off of the aircraft, indicative of the locking pin being disposed within the aperture, establishing the locked state of the extended landing gear assembly.

2. The landing gear monitoring and alerting system of claim 1 , further comprising a display device within a primary field of view in a cockpit of the aircraft, the display device being configured to display information about the locking pin being disposed within the aperture to establish the locked state of the extended landing gear assembly, in response to the transmitted signal being received by the display device via a data network of the aircraft.

3. The landing gear monitoring and alerting system of claim 1 , wherein the magnetic sensor comprises a magnetic sensor-activated switch, wherein the magnetic sensor is configured to activate the magnetic sensor-activated switch upon magnetically sensing that the locking pin is disposed within the aperture, and provide the sensor output to the communication module.

4. The landing gear monitoring and alerting system of claim 1 , wherein the at least one linkage includes a pair of pivotally coupled linkage members, the aperture extends through the pair of pivotally coupled linkage members, and the locking pin is configured to be inserted within the aperture extending through the pair of pivotally coupled linkage members to inhibit movement of the pair of pivotally coupled linkage members relative to each other such that the pair of pivotally coupled linkage members are held in fixed relation to each other.

5. The landing gear monitoring and alerting system of claim 1 , wherein the communication module comprises a microcontroller configured to receive the sensor output from the magnetic sensor, and the communication module includes integrated wifi components configured to wirelessly transmit the signal indicative of the locking pin being disposed within the aperture.

6. The landing gear monitoring and alerting system of claim 5 , wherein the microcontroller is a universal host controller interface that transmits the signal indicative of the locking pin being disposed within the aperture via a universal asynchronous receiver-transmitter.

7. The landing gear monitoring and alerting system of claim 1 , wherein the communication module is configured to transmit the signal, prior to take-off of the aircraft, indicative of the locking pin being disposed within the aperture to a ground crew handheld device in response to receiving the sensor output indicative of the locking pin being disposed within the aperture.

8. The landing gear monitoring and alerting system of claim 1 , wherein the communication module comprises a microcontroller configured to determine whether a flight phase has transitioned to taxiing based on a signal from a flight management system, and responsive to transitioning to taxiing, the communication module is configured to transmit the signal indicative of the locking pin being disposed within the aperture in response to receiving the sensor output indicative of the locking pin being disposed within the aperture and receiving flight phase information indicative of a taxiing movement by the aircraft.

9. The landing gear monitoring and alerting system of claim 1 , further comprising a display device within a primary field of view in a cockpit of the aircraft, the display device being configured to display information about the locking pin being disposed within the aperture to establish the locked state of the extended landing gear assembly on a synoptic page, in response to the transmitted signal being received by the display device via a data network of the aircraft.

10. A method of operating a landing gear monitoring and alerting system of an aircraft, the method comprising:
monitoring a magnetic field proximate an aperture of a landing gear assembly, the landing gear assembly including at least one linkage, the aperture extending through the at least one linkage, the landing gear assembly including a locking pin configured to be inserted into the aperture when the landing gear assembly is in an extended position to inhibit movement of the at least one linkage and establish a locked state of the landing gear assembly in the extended position;
actuating a locking actuating rod which drives a locking hook to hook around the locking pin to lock the locking pin in place to inhibit movement of the at least one linkage which locks the landing gear assembly is in the extended position;
sensing a magnetic response indicative of the locking pin being disposed within the aperture, prior to take-off of the aircraft, to establish the locked state of the landing gear assembly in the extended position; and
transmitting a signal, prior to take-off of the aircraft, indicative of the locking pin being inserted into the aperture, establishing the locked state of the landing gear assembly in response to sensing the magnetic response indicative of the locking pin being disposed within the aperture to establish the locked state of the landing gear assembly in the extended position.

11. The method of claim 10 , further comprising displaying information about the locking pin being disposed within the aperture on a display device of the aircraft in response to the transmitted signal being received by the display device via a data network of the aircraft, and the display device having a primary field of view in a cockpit of the aircraft.

12. The method of claim 10 , wherein sensing the magnetic response includes activating a magnetic sensor-activated switch upon magnetically sensing that the locking pin is disposed within the aperture and transmitting a sensor output from the magnetic sensor-activated switch to a communication module of the landing gear monitoring and alerting system in response to activating the magnetic sensor-activated switch.

13. The method of claim 10 , wherein transmitting the signal indicative of the locking pin being inserted into the aperture includes wirelessly transmitting the signal indicative of the locking pin being inserted into the aperture.

14. The method of claim 10 , wherein transmitting the signal indicative of the locking pin being inserted into the ape

Assignees

• Boeing Co

Inventors

• Kamat Ameya D
• Anstey Tim W
• Durairaj Surya Sundar Raj

Classifications

• B64D45/06 Primary

  mechanical · CPC title

• B64D43/00

  Arrangements or adaptations of instruments · CPC title

• B64D45/0005

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

• B64D2045/0085

  Devices for aircraft health monitoring, e.g. monitoring flutter or vibration · CPC title

• B64C25/26 Primary

  Control or locking systems therefor · CPC title