System and method for conditioning a power source of an electric vehicle

1 . A system for preconditioning a power source of an electric aircraft, wherein the system comprises:

a ground service equipment, wherein the ground service equipment is configured to precondition a power source of an electric aircraft and comprises:

a first pump configured to pump a coolant between the power source and the ground service equipment for changing a temperature of the power source, wherein the first pump is a positive pressure pump; and

a second pump configured to pump at least a portion of the coolant out of the power source prior to takeoff of the aircraft, wherein the second pump is a negative pressure pump; and

a controller communicatively connected to the ground service equipment, wherein the controller is configured to:

control the first pump during a preconditioning process; and

control the second pump during a coolant removal process;

the system further comprising a flow sensor measuring a flow rate of the coolant, wherein the controller is communicatively connected to the flow sensor, and wherein the controller is further configured to:

receive the flow rate from the sensor;

control the positive pressure pump to pump the coolant into the power source responsive to at least the flow rate; and

control the negative pressure pump to pump the coolant out of the power source responsive to at least the flow rate.

2 . The system of claim 1 , wherein:

the first pump is configured to pump a coolant into the power source; and

the second pump is configured to reduce a pressure in the power source below a pressure of a surrounding environment of the power source to at least pump the coolant out of the power source; and

the controller is further configured to:

control the positive pressure pump to pump the coolant into the power source; and

control the negative pressure pump to reduce the pressure in the power source below the pressure of the surrounding environment of the power source to at least pump the coolant out of the power source.

3 . The system of claim 2 , wherein the power source of the electric aircraft comprises a cooling circuit configured to allow a coolant flow, wherein the positive pressure pump is further configured to pump the coolant from at least a coolant reservoir into the cooling circuit of the power source.

4 . The system of claim 3 , wherein the negative pressure pump is configured to pump the coolant to the at least a coolant reservoir.

5 . The system of claim 2 , wherein the negative pressure pump is further configured to reduce the pressure in the power source below the pressure of the surrounding environment of the power source to pump the coolant out of the cooling circuit of the power source.

6 . The system of claim 2 , wherein the negative pressure pump is configured to reduce the pressure in the power source below the pressure of the surrounding environment of the power source to pull the coolant out of the power source after the positive pressure pump pumps the coolant into the power source of the electric aircraft from at least the coolant reservoir.

7 . The system of claim 1 , wherein the flow sensor includes a mass flow rate sensor.

8 . The system of claim 1 , further comprising a temperature sensor configured to measure a temperature of the coolant, wherein the temperature sensor is communicatively connected to the controller, and wherein the controller is further configured to control at least one of the positive pressure pump or the negative pressure pump responsive to the temperature of the coolant.

9 . A method for preconditioning a power source of an electric aircraft, wherein the method comprises:

receiving, using a controller, a predefined power source temperature;

receiving, using the controller, a temperature of a power source of an electric aircraft from at least a sensor communicatively connected to the power source;

receiving, using the controller, one of:

a flow rate of the coolant measured by a flow sensor communicatively connected to the controller; or

a temperature of the coolant measured by a temperature sensor communicatively connected to the controller;

controlling, using the controller, a first pump of ground service equipment to pump a coolant into the power source of the electric aircraft as a function of the temperature of the power source and the predefined power source temperature, wherein the first pump is a positive pressure pump;

controlling, using the controller, a second pump of the ground service equipment to pump the coolant out of the power source of the electric aircraft of the ground service equipment as a function of the temperature of the power source and the predefined temperature of the power source, wherein the second pump is a negative pressure pump configured to reduce a pressure in the power source below a pressure of a surrounding environment of the power source; and

controlling, using the controller, at least one of the positive pressure pump or the negative pressure pump responsive to the one of the flow rate of the coolant or the temperature of the coolant.

10 . The method of claim 9 , wherein the power source of the electric aircraft comprises a cooling circuit configured to allow a coolant flow, wherein the positive pressure pump is further configured to pump the coolant from at least a coolant reservoir into the cooling circuit of the power source.

11 . The method of claim 9 , further comprising:

pumping, using the negative pressure pump to reduce the pressure in the power source below the pressure of the surrounding environment of the power source, the coolant out of the cooling circuit of the power source.

12 . The method of claim 11 , wherein pumping the coolant out of the cooling circuit of the power source includes pumping the coolant to the at least a coolant reservoir.

13 . The method of claim 9 , wherein controlling, using the controller, the negative pressure pump includes controlling the negative pressure pump to pump the coolant to at least a coolant reservoir.

14 . A system for preconditioning a power source of an electric aircraft, wherein the system comprises:

a ground service equipment, wherein the ground service equipment is configured to precondition a power source of an electric aircraft and comprises:

a first pump configured to pump a coolant from at least a coolant reservoir into the power source;

a second pump configured to pump the coolant out of the power source to the at least a coolant reservoir; and

a flow sensor configured to measure a flow rate of the coolant; and

a controller communicatively connected to the ground service equipment, wherein the controller is configured to:

control the first pump to pump the coolant into the power source responsive to at least the flow rate of the coolant; and

control the second pump to pump the coolant out of the power source responsive to at least the flow rate of the coolant.

15 . The system of claim 14 , wherein:

the first pump is a positive pressure pump configured to pump a coolant into the power source; and

the second pump is a negative pressure pump configured to reduce a pressure in the power source below a pressure of a surrounding environment of the power source to at least pump the coolant out of the power source; and

the controller is further configured to:

control the positive pressure pump to pump the coolant into the power source; and

control the negative pressure pump to reduce the pressure in the power source below the pressure of the surrounding environment of the power source to at least pump the coolant out of the power source.

16 . The system of claim 14 , further comprising a temperature sensor configured to measure a temperature of the coolant, wherein the temperature sensor is communicatively connected to the controller, and wherein the controller is further configured to control at least one of the positive pressure pump or the negative pressure pump responsive to the temperature of the coolant.