Monitoring system for an electric aircraft and a method for its use

Patent metadata

Field	Value
Publication number	US-11941925-B2
Application number	US-202217852783-A
Country	US
Kind code	B2
Filing date	Jun 29, 2022
Priority date	Jun 29, 2022
Publication date	Mar 26, 2024
Grant date	Mar 26, 2024

Abstract

An aircraft monitoring system for an electric aircraft is disclosed. The monitoring system may include at least a sensor configured to generate a failure datum. The failure datum includes a datum regarding a condition of an electric motors. An electronic checklist may include a crew alerting system (CAS). A CAS may be in electronic communication a sensor, wherein the CAS is comprised of at least a computing device. A CAS may generate a plurality of remedy data as a function of the failure datum. A CAS then may display the plurality of remedy data using a pilot display. A pilot may be prompted to apply the remedy datum using a pilot display as a function of the plurality of remedy data. The CAS provides an indication of the condition of the electric motor using a pilot display as a function of the application of the plurality of remedy data.

First claim

What is claimed is:

1. An aircraft monitoring system for an electric aircraft, wherein
the aircraft monitoring system comprises:
at least a sensor configured to generate a failure datum, wherein the failure datum includes a datum regarding a condition of an electric motor;
a crew alerting system (CAS) in electronic communication with the at least a sensor, wherein the CAS is comprised of at least a computing device, wherein the at least a computing device is configured to:
generate a checklist comprising a plurality of branches, each branch comprising a plurality of remedy data configured to address the failure datum for the electric motor;
determine a first branch of the plurality of branches as a function of the failure datum;
display the plurality of remedy data for the first branch using a pilot display, wherein the plurality of remedy data is displayed with increasing intrusiveness from a least intrusive remedy that is expected to be the least intrusive to a flight plan or operation of the aircraft to a most intrusive remedy that is expected to be the most intrusive to a flight plan or operation of the aircraft;
prompt a pilot to apply a remedy datum of the plurality of remedy data for the first branch using the pilot display as a function of the plurality of remedy data, wherein correlations between the failure datum and the remedy datum are generated from past failure data and past remedy data;
apply the remedy datum; and
provide an indication of the condition of the electric motor using the pilot display as a function of the application of the remedy datum.

2. The monitoring system of claim 1 , wherein the computing device is further configured to generate the remedy datum as a function of the indication of the condition of the electric motor.

3. The monitoring system of claim 1 , wherein the indication comprises a failure score.

4. The monitoring system of claim 1 , wherein applying the remedy datum comprises engaging a plurality of temperature regulating devices.

5. The monitoring system of claim 4 , wherein the plurality of temperature regulating elements comprises heating elements.

6. The monitoring system of claim 4 , wherein the plurality of temperature regulating elements includes cooling elements.

7. The monitoring system of claim 1 , wherein the plurality of remedy data is generated using a machine learning model, wherein the machine learning model is trained using training data comprising correlations between a set of failure datum and a set of remedy datum.

8. The monitoring system of claim 1 , wherein the plurality of remedy data is generated using a fuzzy logic.

9. The monitoring system of claim 1 , wherein the failure datum includes a datum regarding a condition of an energy source.

10. The monitoring system of claim 9 , wherein the CAS is further configured to provide an indication of the condition of the energy source using the pilot display as a function of the application of the remedy datum.

11. A method of use for a monitoring system for an electric aircraft, wherein the method comprises:
generating, using at least a senor, a failure datum wherein the failure datum includes a datum regarding a condition of an electric motor;
generating, using a crew alerting system (CAS), a checklist comprising a plurality of branches, each branch comprising a plurality of remedy data configured to address the failure datum for the electric motor;
determining, using the CAS, a first branch of the plurality of branches a function of the failure datum;
displaying, using the CAS, the plurality of remedy data for the first branch using a pilot display, wherein the plurality of remedy data is displayed with increasing intrusiveness from a least intrusive remedy that is expected to be the least intrusive to a flight plan or operation of the aircraft to a most intrusive remedy that is expected to be the most intrusive to a flight plan or operation of the aircraft;
prompting, using the CAS, a pilot to apply a remedy datum of the plurality of remedy data for the first branch using the pilot display as a function of the plurality of remedy data, wherein correlations between the failure datum and the remedy datum are generated from past failure data and past remedy data;
applying, using the CAS, the remedy datum; and
providing, using the CAS, an indication of the condition of the electric motor using the pilot display as a function of the application of the plurality of remedy data.

12. The method of claim 11 , wherein the computing device is further configured to generate the remedy datum as a function of the indication of the condition of the electric motor.

13. The method of claim 11 , wherein the indication comprises a failure score.

14. The method of claim 11 , wherein applying the remedy datum comprises engaging a plurality of temperature regulating devices.

15. The method of claim 14 , wherein the plurality of temperature regulating elements comprises heating elements.

16. The method of claim 14 , wherein the plurality of temperature regulating elements includes cooling elements.

17. The method of claim 11 , wherein the plurality of remedy data is generated using a machine learning model, wherein the machine learning model is trained using training data comprising correlations between a set of failure datum and a set of remedy datum.

18. The method of claim 11 , wherein the plurality of remedy data is generated using a fuzzy logic.

19. The method of claim 11 , wherein the failure datum includes a datum regarding a condition of an energy source.

20. The method of claim 19 , wherein the CAS is further configured to provide an indication of the condition of the energy source using the pilot display as a function of the application of the remedy datum.

Assignees

• Beta Air Llc

Inventors

• Guthrie Charles Camron
• Henck Thomas

Classifications

• G08G5/21

  located onboard the aircraft · CPC title

• G08G5/53

  for cruising · CPC title

• G08G5/58

  for emergency situations, e.g. hijacking or bird strikes · CPC title

• G08G5/55

  for a single aircraft · CPC title

• G07C5/0825 Primary

  using optical means · CPC title