Emergency power generation system for an aircraft

An emergency power generation system for an aircraft, wherein the aircraft includes:

• a fuselage section and/or a wing section;
• a main duct at least partially arranged inside the fuselage section and/or the wing section, the main duct extending from an air inlet to an air outlet, wherein the air inlet and the air outlet are in fluid communication with an exterior of the aircraft and wherein external air enters the air inlet and flows through the main duct;
• and
• a secondary duct at least partially arranged inside the fuselage section and/or the wing section, the secondary duct having a secondary air inlet in fluid communication with the main duct at a connection region of the main duct, wherein the connection region is between the air inlet and the air outlet of the main duct;
• wherein the emergency power generation system comprises:
• a rotating electric machine adapted to be arranged inside the main duct between the air inlet and the connection region of the main duct, wherein the rotating electric machine is configured to operate in:
• a generator mode in which air from the exterior of the aircraft flows through the main duct and induces rotational movement of the rotating electric machine to generate electrical energy, and
• a motor mode in which electric power supplied to the rotating electric machine causes rotational movement of the rotating electric machine;
• a control unit;
• a first switch in communication with the control unit, wherein the first switch is configured to selectively cause the rotating electric machine to operate in the generator mode and the motor mode;
• air outlet actuator in communication with the control unit, wherein the air outlet actuator is configured to selectively open and/or close the air outlet of the main duct;
• an airflow passage controller in communication with the control unit, wherein the airflow passage controller is configured to selectively:
• (i) open the main duct at the connection region and close the inlet of the secondary duct;
• and/or
• (ii) close the main duct at the connection region and open the inlet of the secondary duct;
• wherein the control unit is configured to cause during an emergency mode occurring during flight of the aircraft:
• the first switch to place the rotating electric machine in the generator mode,
• the airflow passage controller to close the inlet of the secondary duct, and
• the air outlet actuator to open the air outlet of the main duct,
• wherein external air from outside the aircraft enters through the air inlet, flows through the main duct, drives rotation of the rotating electric machine and exits from air outlet to outside of the aircraft, and
• wherein the rotation of the rotating electric machine generates electricity supplied to the aircraft.