SYSTEMS AND METHODS FOR A SHUTDOWN OF AN ELECTRIC CHARGER IN RESPONSE TO A FAULT DETECTION
A system for a shutdown of an electric charger of an electric vehicle in response to a fault detection is presented. The system includes a sensor communicatively connected to a charging component, wherein the sensor is configured to detect at least a measured charger datum and generate a sensor datum as a function of the at least a measured charger datum. The system further includes a computing device, wherein the computing device is configured to identify a fault element as a function of the sensor datum, determine a disruption element as a function of the identification of the fault element. and initiate a shutdown protocol of the charging component as a function of the disruption element.
1 . A system for a shutdown of an electric charger of an electric vehicle in response to a fault detection, the system comprising:
a sensor communicatively connected to a charging component, wherein the sensor is configured to:
detect at least a measured charger datum; and
generate a sensor datum as a function of the at least a measured charger datum;
a processor, wherein the processor is configured to:
identify a fault element as a function of the sensor datum;
determine a disruption element as a function of the identification of the fault element;
assign the disruption element with a trip class; and
initiate a shutdown protocol of the charging component as a function of the disruption element and the trip class, wherein the shutdown protocol includes safety lock instructions comprising:
verifying a physical connection between the charging component and an electric aircraft; and
unlocking, if the physical connection is verified, a fastener of the charging component to disconnect the charging component and the electric aircraft.
2 . The system of claim 1 , wherein the electric vehicle further comprises an electric aircraft.
3 . The system of claim 2 , wherein the processor is further configured to receive a battery pack datum from the electric aircraft.
4 . The system of claim 1 , wherein the fault element further comprises a network communication fault.
5 . The system of claim 1 , wherein the fault element further comprises an electrical abnormality.
6 . The system of claim 1 , wherein the processor is further configured to determine the disruption element as a function of a fault threshold.
7 . The system of claim 1 , wherein the shutdown protocol further comprises tripping the charging component, using a switch, as a function of the disruption element.
8 . The system of claim 1 , wherein the processor is configured to initiate the shutdown protocol automatically.
9 . The system of claim 1 , wherein the shutdown protocol further comprises disabling a power supply of the charging component.
10 . The system of claim 1 , wherein the shutdown protocol further comprises an emergency protocol, wherein the emergency protocol includes electrically shutting down at least an electrical connection of the charging component.
11 . A method for a shutdown of an electric charger in response to a fault detection, the method comprising:
detecting, by a sensor communicatively connected to a charging component, at least a measured charger datum;
generating sensor datum as a function of the at least a measured charger datum;
receiving, by a processor, the sensor datum;
identifying a fault element as a function of the sensor datum;
determining a disruption element as a function of the identification of the disruption element;
assigning the disruption element with a trip class; and
initiating a shutdown protocol of the charging component as a function of the disruption element and the trip class, wherein the shutdown protocol includes safety lock instructions comprising:
verifying a physical connection between the charging component and an electric aircraft; and
unlocking, if the physical connection is verified, a fastener of the charging component to disconnect the charging component and the electric aircraft.
12 . The method of claim 11 , wherein the electric vehicle further comprises an electric aircraft.
13 . The method of claim 12 , wherein the method further comprises receiving a battery pack datum from the electric aircraft.
14 . The method of claim 11 , wherein identifying the fault element further comprises identifying a fault within a network communication.
15 . The method of claim 11 , wherein identifying the fault element further comprises identifying an electrical abnormality.
16 . The method of claim 11 , wherein the method further comprises determining the disruption element as a function of a fault threshold.
17 . The method of claim 11 , wherein initiating the shutdown protocol further comprises tripping the charging component as a function of the disruption element using a switch.
18 . The method of claim 11 , wherein the method further comprises initiating the shutdown protocol automatically by the processor.
19 . The method of claim 11 , wherein initiating the shutdown protocol further comprises disabling a power supply of the charging component.
20 . The method of claim 11 , wherein initiating the shutdown protocol further comprises initiating an emergency protocol, wherein the emergency protocol includes shutting down at least an electrical connection of the charging component.