Diode fault detection

Patent metadata

Field	Value
Publication number	US-11239841-B1
Application number	US-202117193883-A
Country	US
Kind code	B1
Filing date	Mar 5, 2021
Priority date	Mar 5, 2021
Publication date	Feb 1, 2022
Grant date	Feb 1, 2022

Abstract

A power delivery system includes a controller, configured to receive a voltage indication signal indicating a measured voltage of a battery management system and to determine whether first and second diodes of the battery management system are faulty based on the voltage indication signal. The controller is also configured to respectively receive first and second current indication signals from first and second current sensors of the battery management system and to determine whether the first and second diodes of the first battery management system are faulty based on the first and second current indication signals.

First claim

The invention claimed is:

1. A power delivery system for an aircraft, the power delivery system comprising:
a plurality of battery management systems, each comprising:
a battery system,
first and second diodes configured to conduct current from the battery system to a power supply node,
a first current sensor configured to sense a first current of the first diode,
a second current sensor configured to sense a second current of the second diode,
a first switch configured to control a conductivity of a first current path between the battery system and the first and second diodes, and
a second switch configured to control a conductivity of a second current path between the battery system and the first and second diodes; and

a controller, wherein the controller is configured to receive a voltage indication signal indicating a measured voltage of a first battery management system of the battery management systems and to determine whether the first and second diodes of the first battery management system are faulty based on the voltage indication signal, and wherein the controller is configured to respectively receive first and second current indication signals from the first and second current sensors of the first battery management system and to determine whether the first and second diodes of the first battery management system are faulty based on the first and second current indication signals.

2. The power delivery system of claim 1 , wherein the controller is configured to determine whether the first and second diodes are open based on the voltage indication signal.

3. The power delivery system of claim 1 , wherein the controller is configured to determine whether either of the first and second diodes are shorted based on the voltage indication signal.

4. The power delivery system of claim 1 , wherein the first current path has a first impedance when conductive, wherein the second current path has a second impedance when conductive, and wherein the first impedance is greater than the second impedance.

5. The power delivery system of claim 1 , wherein the controller is configured to electrically connect the battery system of a second battery management system to the power supply node, and to determine whether either of the first and second diodes of the first battery management system are shorted based on the voltage indication signal.

6. The power delivery system of claim 5 , wherein the controller is configured to determine that either or both of the first and second diodes of the first battery management system are shorted based on the voltage indication signal indicating that the measured voltage of the first battery management system is greater than a threshold.

7. The power delivery system of claim 5 , wherein the controller is configured to determine whether either of the first and second diodes of the first battery management system are shorted during a preflight test while the aircraft is not flying.

8. The power delivery system of claim 1 , wherein the controller is configured to electrically connect the battery system of the first battery management system to the first and second diodes of the first battery management system, to electrically disconnect the battery system of the first battery management system from the first and second diodes of the first battery management system, and to determine whether either of the first and second diodes of the first battery management system are open based on the voltage indication signal.

9. The power delivery system of claim 8 , wherein the controller is configured to determine that the first and second diodes of the first battery management system are open based on the voltage indication signal indicating that the measured voltage of the first battery management system is greater than a threshold.

10. The power delivery system of claim 8 , wherein the controller is configured to determine whether either of the first and second diodes of the first battery management system are open during a preflight test while the aircraft is not flying.

11. The power delivery system of claim 1 , wherein the controller is configured to determine whether either of the first and second diodes of the first battery management system is open based on the first and second current indication signals.

12. The power delivery system of claim 11 , wherein the controller is configured to determine whether the first diode of the first battery management system is open based on the first current indication signal being less than a threshold, and wherein the controller is configured to determine whether the second diode of the first battery management system is open based on the second current indication signal being less than the threshold.

13. The power delivery system of claim 11 , wherein the controller is configured to determine whether either of the first and second diodes of the first battery management system is open while the aircraft is flying.

14. The power delivery system of claim 1 , wherein the controller is configured to determine whether either of the first and second diodes is shorted based on the first and second current indication signals.

15. The power delivery system of claim 14 , wherein the controller is configured to determine whether the first diode of the first battery management system is shorted based on the first current indication signal being greater than a threshold, and wherein the controller is configured to determine whether the second diode of the first battery management system is shorted based on the second current indication signal being greater than the threshold.

16. The power delivery system of claim 14 , wherein the controller is configured to determine whether either of the first and second diodes of the first battery management system is shorted while the aircraft is flying.

17. A method of operating a power delivery system for an aircraft, the power delivery system comprising: a plurality of battery management systems, each comprising: a battery system, and first and second diodes configured to conduct current from the battery system to a power supply node, the method comprising:
with a controller, receiving a voltage indication signal indicating a measured voltage of a first battery management system of the battery management systems;
with the controller, determining whether the first and second diodes of the first battery management system are faulty based on the voltage indication signal;
with the controller, respectively receiving first and second current indication signals from the first battery management system; and
with the controller, determining whether the first and second diodes of the first battery management system are faulty based on the first and second current indication signals.

18. The method of claim 17 , wherein the controller is configured to determine whether either of the first and second diodes of the first battery management system is shorted based on the first and second current indication signals while the aircraft is flying.

19. The method of claim 17 , wherein the controller is configured to determine whether either of the first and second diodes of the first battery management system is open based on the first and second current indication signals while the aircraft is flying.

20. The method of claim 17 , wherein the controller is configured to determine whether either of the first and second diodes of the first battery management system is shorted based on the voltage indication signal while the aircraft is not flying.

Assignees

• Wisk Aero Llc

Inventors

• Chen Hongxia
• Gao Rui
• Hom Lewis Romeo
• Long Geoffrey Alan

Classifications

• H03K2217/0081

  Power supply means, e.g. to the switch driver · CPC title

• H03K17/74 Primary

  by the use, as active elements, of diodes (by the use of more than one type of semiconductor device H03K17/567; by the use of tunnel diodes H03K17/58; by the use of negative resistance diodes H03K17/70) · CPC title

• H03K17/0822 Primary

  in field-effect transistor switches · CPC title