Systems and methods for an electric aircraft charging connector
An electric aircraft charging connector, including a direct current pin and/or an alternating current pin. The connector including a ground pin, the ground pin providing a grounded connection. The connector also including a resistance sensor, the resistance sensor electrically connected to the direct current pin and/or the alternating current pin, and the ground pin, the resistance sensor configured to measure a resistance datum, the resistance datum including: a first resistance, the first resistance comprising a measurement of resistance between the direct current pin and the ground pin; and a second resistance, the second resistance comprising a measurement of resistance between the alternating current pin and the ground pin. The connector also including a controller, the controller configured to: receive the resistance datum from the resistance sensor; and compare the resistance datum to a threshold resistance datum.
1. An electric aircraft charging connector, comprising:
a direct current pin;
an alternating current pin;
a ground pin, the ground pin providing a grounded connection;
a resistance sensor, the resistance sensor electrically connected to the direct current pin, the alternating current pin, and the ground pin, the resistance sensor configured to measure a resistance datum, the resistance datum comprising:
a first resistance, the first resistance comprising a measurement of resistance between the direct current pin and the ground pin; and
a second resistance, the second resistance comprising a measurement of resistance between the alternating current pin and the ground pin; and
a controller, the controller configured to:
receive the resistance datum from the resistance sensor; and
compare the resistance datum to a threshold resistance datum.
2. The electric aircraft charging connector of claim 1 , comprising a switch, the switch having an engaged state and a disengaged state.
3. The electric aircraft charging connector of claim 2 , wherein:
the switch, in its engaged state, forms an electronic connection to a load; and
the switch, in its disengaged state, is not electronically connected to the load.
4. The electric aircraft charging connector of claim 3 , wherein the load is an energy storage device.
5. The electric aircraft charging connector of claim 2 , wherein the switch is a circuit breaker.
6. The electric aircraft charging connector of claim 2 , wherein the switch is a relay.
7. The electric aircraft charging connector of claim 2 , wherein the controller is further configured to disengage the switch when the resistance datum is less than the threshold resistance datum.
8. The electric aircraft charging connector of claim 7 , wherein the controller is further configured to engage the switch in response to a command.
9. The electric aircraft charging connector of claim 8 , wherein the command is initiated by a user.
10. The electric aircraft charging connector of claim 7 , further comprising a proximity detection pin, and wherein the controller is further configured to:
receive a current datum from the proximity detection pin; and
engage the switch when the current datum is zero.
11. The electric aircraft charging connector of claim 7 , wherein the controller is further configured to display a visual alert on a display.
12. The electric aircraft charging connector of claim 7 , wherein the controller is further configured to send an audio alert.
13. The electric aircraft charging connector of claim 1 , wherein the direct current pin comprises a direct current live pin and a direct current neutral pin, the direct current live pin supplying direct current power, the direct current neutral pin providing a return path for the direct current power.
14. The electric aircraft charging connector of claim 1 , wherein the alternating current pin comprises an alternating current live pin and an alternating current neutral pin, the alternating current live pin supplying direct current power, the alternating current neutral pin providing a return path for the direct current power.
15. A method of monitoring an electric aircraft charging connector, comprising:
receiving, by a controller of a charging connector, a first resistance, the first resistance comprising a measurement of resistance between a direct current pin and a ground pin of the charging connector;
receiving, by the controller, a second resistance, the second resistance comprising a measurement of resistance between an alternating current pin and a ground pin of the charging connector;
comparing, by the controller, the first resistance to a threshold resistance datum; and
disengaging, by the controller, a switch if the first resistance is less than the threshold resistance datum.
16. The method of monitoring an electric aircraft charging connector of claim 15 , further comprising:
comparing the second resistance to a threshold resistance datum; and
disengaging the switch if the second resistance is less than the threshold resistance datum.
17. The method of monitoring an electric aircraft charging connector of claim 16 , further comprising engaging the switch in response to a command initiated by a user.
18. The method of monitoring an electric aircraft charging connector of claim 16 , further comprising:
receiving a current datum from a proximity detection pin; and
engaging the switch if the current datum is zero.
19. The method of monitoring an electric aircraft charging connector of claim 16 , further comprising displaying a visual alert on a display.
20. The method of monitoring an electric aircraft charging connector of claim 16 , further comprising sending an audio alert.