Systems and methods for battery charging mode selection
A control system for charging an aircraft, comprising: a battery pack, an input device configured to enable a user to select between different charging modes, two main contactors connecting the battery pack to an electric propulsion unit (EPU) load and an auxiliary load, a EPU load contactor connecting the battery pack to the EPU load and a controller configured to receive the selected charge mode and control the contactors, keep the two main contactors open upon receiving a user selection to charge in a first mode, close the two main contactors and keep an EPU load contactor open upon receiving a user selection to charge in a second mode, and close the two main contactors and the EPU load contactor upon receiving a user selection to charge in a third mode.
1 . A control system for charging an aircraft, comprising:
a battery pack;
an input device configured to enable a user to select between different charging modes;
two main contactors connecting the battery pack to an electric propulsion unit (EPU) load and a non-propulsive load;
an EPU load contactor connecting the battery pack to the EPU load; and a controller configured to receive the selected charge mode and control the contactors, wherein the controller is further configured to:
keep the two main contactors open, causing the EPU load and the non-propulsive load to remain disconnected, upon receiving a user selection to charge in a first mode;
close the two main contactors and keep the EPU load contactor open, connecting the non-propulsive load and causing the EPU load to remain disconnected, upon receiving a user selection to charge in a second mode; and
close the two main contactors and the EPU load contactor, connecting the non-propulsive load and the EPU load, upon receiving a user selection to charge in a third mode.
2 . The control system of claim 1 , wherein the input device is a physical switch, button, or lever.
3 . The control system of claim 1 , wherein the input device is a user interface element output at a display.
4 . The control system of claim 1 , wherein the controller is further configured to monitor a state of the battery pack and adjust the charging mode based on feedback from the battery pack.
5 . The control system of claim 1 , wherein the controller is further configured to prevent charging if a fault condition is detected in the battery pack.
6 . The control system of claim 5 , wherein the fault condition includes at least one of an overcurrent, an overvoltage, or a temperature exceeding a predetermined threshold.
7 . The control system of claim 1 , further comprising a thermal management module that is configured to adjust a charging process for the battery pack by sending cooling commands to an external system based on a temperature of the battery pack.
8 . The control system of claim 1 , wherein the control system is configured to adjust the charging mode for future sessions to optimize battery health and charging efficiency after analyzing historical data from previous charging sessions.
9 . The system of claim 1 , wherein the controller is configured to enable communication between the battery pack and another battery pack, wherein the communication allows the battery packs to share information about their respective states to help determine an overcurrent condition.
10 . The control system of claim 1 , wherein the control system is configured to activate a redundant active trigger board that enables a pyro fuse driver to trigger one or more pyrotechnical fuses when the controller fails to activate the pyro fuse driver.
11 . A controller for charging an aircraft, wherein the controller is configured to:
receive a charge mode from an input device configured to enable a user to select between different charging modes;
control two main contactors connecting a battery pack to an electric propulsion unit (EPU) load and a non-propulsive load;
control an EPU load contactor connecting the battery pack to the EPU load;
keep the two main contactors open, causing the EPU load and the non-propulsive load to remain disconnected, upon receiving a user selection to charge in a first mode;
close the two main contactors and keep an EPU load contactor open, connecting the non-propulsive load and causing the EPU load to remain disconnected, upon receiving a user selection to charge in a second mode; and
close the two main contactors and the EPU load contactor, connecting the non-propulsive load and the EPU load, upon receiving a user selection to charge in a third mode.
12 . The controller of claim 11 , wherein the input device is a physical switch, button, or lever.
13 . The controller of claim 11 , wherein the input device is a user interface element output at a display.
14 . The controller of claim 11 , wherein the controller is further configured to monitor a state of the battery pack and adjust the charging mode based on feedback from the battery pack.
15 . The controller of claim 11 , wherein the controller is further configured to prevent charging if a fault condition is detected in the battery pack.
16 . The controller of claim 15 , wherein the fault condition includes at least one of an overcurrent, an overvoltage, or a temperature exceeding a predetermined threshold.
17 . The controller of claim 15 , wherein the fault condition is based on information received from a current sensor.
18 . The controller of claim 11 , wherein the controller is powered by the battery pack.
19 . The controller of claim 11 , wherein the controller is configured to enable communication between the battery pack and another battery pack, wherein the communication allows the battery packs to share information about their respective states to help determine an overcurrent condition.
20 . The controller of claim 11 , wherein the controller is configured to activate a redundant active trigger board that enables a pyro fuse driver to trigger one or more pyrotechnical fuses when the controller fails to activate the pyro fuse driver.