Abstract: There is provided a center fuel tank assembly for an aircraft. The assembly includes a center fuel tank disposed in a central part of the aircraft. The assembly further includes one or more fuel barrier members partitioning the center fuel tank into two or more separate volume sections comprising two or more separate sub-tanks arranged in a fore-to-aft alignment to form a partitioned center fuel tank. The assembly further includes a fuel flow control assembly coupled to each of the two or more separate sub-tanks, each fuel flow control assembly operating independently. A sequential fuel burn of fuel in the two or more separate sub-tanks is made in a fore-to-aft sequence while the aircraft is in flight, to assist in shifting aftward a center of gravity (CG) of the aircraft, to reduce aircraft drag.

Abstract: There is provided a center fuel tank assembly for an aircraft. The assembly includes a center fuel tank disposed in a central part of the aircraft. The assembly further includes one or more fuel barrier members partitioning the center fuel tank into two or more separate volume sections comprising two or more separate sub-tanks arranged in a fore-to-aft alignment to form a partitioned center fuel tank. The assembly further includes a fuel flow control assembly coupled to each of the two or more separate sub-tanks, each fuel flow control assembly operating independently. A sequential fuel burn of fuel in the two or more separate sub-tanks is made in a fore-to-aft sequence while the aircraft is in flight, to assist in shifting aftward a center of gravity (CG) of the aircraft, to reduce aircraft drag.

Abstract: A cooling system for a fuel tank of an aircraft includes a temperature sensor, a cooling system, and a control module. The temperature sensor detects a fuel temperature within the fuel tank. The cooling system maintains the fuel temperature below a control temperature. The phase change cooling system includes a heat exchanger. A cooling fluid flows through the heat exchanger and is in thermal communication with a surface of the fuel tank. The control module is in signal communication with the temperature sensor and the cooling system. The control module includes control logic for monitoring the temperature sensor, determining if the fuel temperature is above the control temperature, and generating an activation signal.

Abstract: A cooling system for a fuel tank of an aircraft includes a temperature sensor, a cooling system, and a control module. The temperature sensor detects a fuel temperature within the fuel tank. The cooling system maintains the fuel temperature below a control temperature. The phase change cooling system includes a heat exchanger. A cooling fluid flows through the heat exchanger and is in thermal communication with a surface of the fuel tank. The control module is in signal communication with the temperature sensor and the cooling system. The control module includes control logic for monitoring the temperature sensor, determining if the fuel temperature is above the control temperature, and generating an activation signal.