Frangible antenna mount electrical interconnect for aircraft components, with break detection

Patent metadata

Field	Value
Publication number	US-12241945-B2
Application number	US-202218059100-A
Country	US
Kind code	B2
Filing date	Nov 28, 2022
Priority date	Nov 28, 2022
Publication date	Mar 4, 2025
Grant date	Mar 4, 2025

Abstract

Systems, apparatuses and methods may provide for a frangible sensor assembly that includes a circuit board having a retained section, a frangible portion, and a detachable section separated from the retained section by the frangible portion, a conductive element on the retained section that spans the frangible portion, and a sensor sub-assembly electrically coupled to the conductive element. The sensor sub-assembly monitors a continuity signal via the conductive element, detects a break of the frangible portion based on the continuity signal, and generates an alert notification in response to the break of the frangible portion.

First claim

We claim:

1. An unmanned aerial vehicle (UAV) comprising:
a fuselage; and
a plurality of wings, at least one of the plurality of wings including a frangible sensor assembly comprising:
a circuit board including a retained section, a frangible portion, and a detachable section separated from the retained section by the frangible portion, wherein the detachable section includes an antenna connector exchanging first signals with one or more of a radio frequency (RF) connector or a motor connector that exchanges second signals with a servo conductor, wherein the antenna connector is electrically coupled with a first antenna,
a conductive element on the retained section that spans the frangible portion, and
a sensor sub-assembly electrically coupled to the conductive element, wherein the sensor sub-assembly is to monitor a continuity signal via the conductive element, detect a break of the frangible portion based on the continuity signal, generate an alert notification in response to the break of the frangible portion, and re-route signals associated with the detachable section in response to the break of the frangible portion being detected by re-routing one or more of the first or second signals to one or more of a second antenna or a motor.

2. The UAV of claim 1 , wherein the alert notification is one or more of a maintenance alert or an in-flight alert.

3. The UAV of claim 1 , wherein the sensor sub-assembly is further to activate one or more back-up systems associated with the detachable section in response to the break of the frangible portion.

4. The UAV of claim 1 , wherein the detachable section includes one or more of an antenna connector or a motor connector.

5. The UAV of claim 1 , wherein the frangible portion includes surfaces defining one or more notches.

6. The UAV of claim 1 , wherein the frangible portion includes surfaces defining a plurality of openings.

7. The UAV of claim 1 , wherein the sensor sub-assembly includes a sensor component and a processor coupled to the sensor component.

8. A frangible sensor assembly comprising:
a circuit board including a retained section, a frangible portion, and a detachable section separated from the retained section by the frangible portion, wherein the detachable section includes an antenna connector exchanging first signals with one or more of a radio frequency (RF) connector or a motor connector that exchanges second signals with a servo conductor, wherein the antenna connector is electrically coupled with a first antenna;
a conductive element on the retained section that spans the frangible portion; and
a sensor sub-assembly electrically coupled to the conductive element, wherein the sensor sub-assembly is to monitor a continuity signal via the conductive element, detect a break of the frangible portion based on the continuity signal, generate an alert notification in response to the break of the frangible portion, and re-route signals associated with the detachable section in response to the break of the frangible portion being detected by re-routing one or more of the first or second signals to one or more of a second antenna or a motor.

9. The frangible sensor assembly of claim 8 , wherein the alert notification is one or more of a maintenance alert or an in-flight alert.

10. The frangible sensor assembly of claim 8 , wherein the sensor sub-assembly is further to activate one or more back-up systems associated with the detachable section in response to the break of the frangible portion.

11. The frangible sensor assembly of claim 8 , wherein the detachable section includes one or more of an antenna connector or a motor connector.

12. The frangible sensor assembly of claim 8 , wherein the frangible portion includes surfaces defining one or more notches.

13. The frangible sensor assembly of claim 8 , wherein the frangible portion includes surfaces defining a plurality of openings.

14. The frangible sensor assembly of claim 8 , wherein the sensor sub-assembly includes a sensor component and a processor coupled to the sensor component.

15. At least one non-transitory computer readable storage medium comprising a set of instructions, which when executed by a processor, cause the processor to:
monitor a continuity signal via a conductive element, wherein the conductive element is on a retained section of a circuit board and spans a frangible portion of the circuit board, and wherein a detachable section of the circuit board is separated from the retained section by the frangible portion;
exchanging, with an antenna connector on the detachable section, first signals with one or more of a radio frequency (RF) connector or a motor connector that exchanges second signals with a servo conductor, wherein the antenna connector is electrically coupled with a first antenna;
detect a break of the frangible portion based on the continuity signal;
generate an alert notification in response to the break of the frangible portion; and
re-route signals associated with the detachable section in response to the break of the frangible portion being detected by re-routing one or more of the first or second signals to one or more of a second antenna or a motor.

16. The at least one non-transitory computer readable storage medium of claim 15 , wherein the alert notification is one or more of a maintenance alert or an in-flight alert.

17. The at least one non-transitory computer readable storage medium of claim 15 , wherein the instructions, when executed, further cause the processor to activate one or more back-up systems associated with the detachable section in response to the break of the frangible portion.

18. The UAV of claim 1 , wherein the first and second signals are rerouted to one or more of the second antenna or the motor.

19. The frangible sensor assembly of claim 8 , wherein the first and second signals are rerouted to one or more of the second antenna or the motor.

20. The at least one non-transitory computer readable storage medium of claim 15 , wherein the first and second signals are rerouted to one or more of the second antenna or the motor.

Assignees

• Boeing Co

Inventors

• Mack Torsten
• Miller Douglas Allyn

Classifications

• G01D3/08

  with provision for safeguarding the apparatus, e.g. against abnormal operation, against breakdown · CPC title

• B64U70/30

  for capturing UAVs in flight by ground or sea-based arresting gear, e.g. by a cable or a net · CPC title

• H01Q1/28

  Adaptation for use in or on aircraft, missiles, satellites, or balloons · CPC title

• G01R31/54 Primary

  Testing for continuity · CPC title