Abstract: A noncombustible gas distribution method includes distributing noncombustible gas to a center wing tank throughout a continuous, first flight period and, as a result, reducing flammability exposure time during the first flight period or during a subsequent flight period. The method includes not distributing noncombustible gas to left and right main wing tanks while the noncombustible gas is distributed to the center wing tank throughout the first flight period and while the left and right main wing tanks are non-flammable. A noncombustible gas distribution system includes a noncombustible gas source and distribution tubing from the gas source to left and right main wing tanks and a center wing tank. A distribution mechanism yields a greater proportion of gas flow per tank unit volume distributed to an outboard section of the left and right main wing tanks compared to an inboard section during a climb phase of the aircraft's flight.

Abstract: A noncombustible gas distribution method includes distributing noncombustible gas to a center wing tank throughout a continuous, first flight period and, as a result, reducing flammability exposure time during the first flight period or during a subsequent flight period. The method includes not distributing noncombustible gas to left and right main wing tanks while the noncombustible gas is distributed to the center wing tank throughout the first flight period and while the left and right main wing tanks are non-flammable. A noncombustible gas distribution system includes a noncombustible gas source and distribution tubing from the gas source to left and right main wing tanks and a center wing tank. A distribution mechanism yields a greater proportion of gas flow per tank unit volume distributed to an outboard section of the left and right main wing tanks compared to an inboard section during a climb phase of the aircraft's flight.

Abstract: A noncombustible gas distribution method includes distributing noncombustible gas to a center wing tank throughout a continuous, first flight period and, as a result, reducing flammability exposure time during the first flight period or during a subsequent flight period. The method includes not distributing noncombustible gas to left and right main wing tanks while the noncombustible gas is distributed to the center wing tank throughout the first flight period and while the left and right main wing tanks are non-flammable. A noncombustible gas distribution system includes a noncombustible gas source and distribution tubing from the gas source to left and right main wing tanks and a center wing tank. A distribution mechanism yields a greater proportion of gas flow per tank unit volume distributed to an outboard section of the left and right main wing tanks compared to an inboard section during a climb phase of the aircraft's flight.

Abstract: A noncombustible gas distribution method includes distributing noncombustible gas to a center wing tank throughout a continuous, first flight period and, as a result, reducing flammability exposure time during the first flight period or during a subsequent flight period. The method includes not distributing noncombustible gas to left and right main wing tanks while the noncombustible gas is distributed to the center wing tank throughout the first flight period and while the left and right main wing tanks are non-flammable. A noncombustible gas distribution system includes a noncombustible gas source and distribution tubing from the gas source to left and right main wing tanks and a center wing tank. A distribution mechanism yields a greater proportion of gas flow per tank unit volume distributed to an outboard section of the left and right main wing tanks compared to an inboard section during a climb phase of the aircraft's flight.

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.

Abstract: An aircraft fuel tank flammability reduction method includes feeding pressurized air into an air separation module containing an oxygen separation membrane. The method includes contacting the separation membrane with the air feed, permeating oxygen from the air feed through the separation membrane, and producing nitrogen-enriched air from the air separation module as a result of removing oxygen from the air feed. The NEA from the air separation module is substantially cooled in a NEA flow heat exchanger and the substantially cooled, nitrogen-enriched air is fed into the fuel tank on board the aircraft. An aircraft fuel tank flammability reduction system includes a NEA flow heat exchanger configured to cool substantially the nitrogen-enriched air from the air separation module and a fuel tank on board the aircraft configured to receive the cooled nitrogen-enriched air.

Abstract: An aircraft fuel tank flammability reduction method includes feeding pressurized air into an air separation module containing an oxygen separation membrane. The method includes contacting the separation membrane with the air feed, permeating oxygen from the air feed through the separation membrane, and producing nitrogen-enriched air from the air separation module as a result of removing oxygen from the air feed. The NEA from the air separation module is substantially cooled in a NEA flow heat exchanger and the substantially cooled, nitrogen-enriched air is fed into the fuel tank on board the aircraft. An aircraft fuel tank flammability reduction system includes a NEA flow heat exchanger configured to cool substantially the nitrogen-enriched air from the air separation module and a fuel tank on board the aircraft configured to receive the cooled nitrogen-enriched air.

Abstract: An inerting system (10) for an aircraft (12) includes one or more fuel tank circuits (15) associated with fuel tanks (16). An air source (17) supplies pressurized air. A heat exchanger (56) cools the pressurized air. An air separation module (46) is in fluid communication with the heat exchanger (56) and separates inerting gas from the pressurized air. A controller (40) controls flow of the inerting gas from the air separation module (46) to the fuel tanks (16).

Abstract: An inerting system (10) for an aircraft (12) includes one or more fuel tank circuits (15) associated with fuel tanks (16). An air source (17) supplies pressurized air. A heat exchanger (56) cools the pressurized air. An air separation module (46) is in fluid communication with the heat exchanger (56) and separates inerting gas from the pressurized air. A controller (40) controls flow of the inerting gas from the air separation module (46) to the fuel tanks (16).