Aircraft thermal management system

An aircraft comprising:

• a fuselage comprising a cabin;
• one or more electric motors configured to drive one or more propulsion systems of the aircraft, wherein the one or more electric motors are configured to generate thermal energy by generating electrical energy in response to a deceleration of the aircraft;
• one or more resistors configured to dissipate the thermal energy to air proximate to the one or more resistors based on the electrical energy;
• an aircraft thermal management system comprising a resistor temperature sensor configured to measure a resistor temperature of the one or more resistors;
• and
• a fan configured to circulate the air proximate to the one or more resistors;
• wherein the aircraft thermal management system is configured to control a valve to direct the circulated air to the cabin if a combination of at least one measurement from the resistor temperature sensor and at least one measurement from a cabin temperature sensor indicates that the resistor temperature is greater than a temperature of the cabin.

An aircraft comprising:

• a fuselage comprising:
• one or more fuselage sections;
• one or more electric motors configured to drive one or more propulsion systems of the aircraft, wherein the one or more electric motors are configured to generate thermal energy by generating electrical energy in response to a deceleration of the aircraft;
• one or more resistors configured to dissipate the thermal energy to air proximate to the one or more resistors based on the electrical energy;
• an aircraft thermal management system configured to transfer the thermal energy generated by the one or more electric motors to the one or more fuselage sections and comprising a resistor temperature sensor configured to measure a resistor temperature of the one or more resistors, wherein the aircraft thermal management system comprises a fluid heat transfer system, the fluid heat transfer system comprising:
• a fluid;
• a thermal channel loop comprising one or more thermal channels and having at least a portion disposed at least proximate to the one or more electric motors, wherein the thermal channel loop is configured to allow the fluid to circulate therein and to allow the thermal energy generated by the one or more electric motors to be transferred to the fluid;
• a fluid temperature sensor configured to measure a fluid temperature of the fluid within the thermal channel loop;
• and
• a heat exchanger configured to transfer the thermal energy from the fluid within the thermal channel loop to air proximate to the heat exchanger;
• and
• a fan configured to circulate the air proximate to the heat exchanger;
• wherein the aircraft thermal management system is configured to transfer the thermal energy generated by the one or more electric motors to the one or more fuselage sections using the fluid heat transfer system;
• wherein the aircraft thermal management system is further configured to control a valve to direct the circulated air received from the fan to an air outlet if a combination of one or more measurements from the resistor temperature sensor and one or more measurements from a cabin temperature sensor indicate that the resistor temperature is greater than the cabin temperature.