Emergency high voltage disconnection device for an electric aircraft
A device for emergency disconnection of a high voltage electrical connection between a power source and a high voltage component of an electric aircraft in response to a crash. The device includes a controller, where the controller is configured to receive a sensor datum from a sensor of device, to determine a crash element between and initiate a disconnection protocol as a function of the crash element.
1. An emergency high voltage disconnection device for an electric aircraft, the device comprising:
an electrical connection configured to transfer electrical power from a power source of an electric aircraft, wherein the electrical connection comprises:
a first conductor attached to a power source; and
a second conductor attached to the first conductor;
a safety mechanism connected to the first conductor and the second conductor, the safety mechanism having an enabled position and a disabled position, wherein the safety mechanism is configured to:
allow, in the disabled position, the transfer of electrical power from the first conductor to the second conductor;
terminate, in the enabled position, the electrical connection; a sensor configured to detect a sensor datum; and
a controller, the controller configured to initiate a disconnection protocol as a function of a crash element, wherein:
the crash element is determined as a function of sensor datum; and
the disconnection protocol comprises moving the safety mechanism from the disabled position to the enabled position.
2. The device of claim 1 , wherein the controller is further configured to: receive the sensor datum from the sensor; and
determine the crash element associated with the crash of the electric aircraft as a function of the sensor datum.
3. The device of claim 2 , wherein determining the crash element comprises determining whether the sensor datum is outside of a preconfigured threshold.
4. The device of claim 1 , wherein the controller comprises a battery management system communicatively connected to the safety mechanism.
5. The device of claim 1 , wherein the safety mechanism comprises a pyrotechnical device.
6. The device of claim 1 , wherein the safety mechanism comprises at least a contactor.
7. The device of claim 6 , wherein the at least a contactor comprises a first contactor and an orthogonal contactor, wherein the orientation of the first contactor and the orthogonal contactor are 90 degrees apart.
8. The device of claim 7 , wherein:
the power source comprises a battery pack;
the first contactor is connected to a negative output terminal of the battery pack; and
the orthogonal contactor is connected to a positive output terminal of the battery pack.
9. The device of claim 1 , wherein the sensor comprises an accelerometer.
10. The device of claim 1 , wherein the sensor comprises an inertial measurement unit.
11. A method for emergency disconnection of an electric connection of a power source of an electric aircraft in response to a crash, the method comprising:
providing an emergency high voltage disconnection device, the device comprising: an electrical connection, wherein the electrical connection comprises:
a first conductor attached to a power source; and
a second conductor attached to the first conductor; and
a safety mechanism connected to the first conductor and the second conductor; detecting, by a sensor, a sensor datum;
transferring, in a disabled position of the safety mechanism, electrical power from a power source from the first conductor to the second conductor;
terminating, in an enabled position of the safety mechanism, the electrical connection so that electrical power cannot traverse from the first conductor to the second conductor; and
initiating, by the controller, a disconnection protocol as a function of the crash element, wherein the disconnection protocol comprises instructions that move the safety mechanism from a disabled position to an enabled position to terminate the electrical connection.
12. The method of claim 11 , further comprising:
receiving, by the controller, the sensor datum from the sensor; and
determining, by the controller, the crash element associated with the crash of the electric aircraft as a function of the sensor datum.
13. The method of claim 12 , wherein determining the crash element comprises determining whether the sensor datum is outside of a preconfigured threshold.
14. The method of claim 11 , wherein the controller comprises a battery management system communicatively connected to the safety mechanism.
15. The method of claim 11 , wherein the safety mechanism comprises a pyrotechnical device.
16. The method of claim 11 , wherein the safety mechanism comprises at least a contactor.
17. The method of claim 16 , wherein the at least a contactor comprises a first contactor and an orthogonal contactor, wherein the orientation of the first contactor and the orthogonal contactor are 90 degrees apart.
18. The method of claim 17 , wherein:
the power source comprises a battery pack;
the first contactor is connected to a negative output terminal of the battery pack; and
the orthogonal contactor is connected to a positive output terminal of the battery pack.
19. The method of claim 11 , wherein the sensor comprises an accelerometer.
20. The method of claim 11 , wherein the sensor comprises an inertial measurement unit.