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.

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.

An isolator for an aircraft fuel tank configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel. The isolator includes: a plurality of first attachment points for attaching the isolator to the panel, a plurality of second attachment points for attaching the isolator to the pipe, and an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator. The aperture is configured to receive the pipe in use, wherein the isolator is formed of a non-electrically conductive material.

An isolator for an aircraft fuel tank configured to separate an electrically conductive internal panel of the fuel tank from an electrically conductive pipe that passes through the panel. The isolator includes: a plurality of first attachment points for attaching the isolator to the panel, a plurality of second attachment points for attaching the isolator to the pipe, and an aperture defined by an outer wall and extending from a first side of the isolator to a second side of the isolator. The aperture is configured to receive the pipe in use, wherein the isolator is formed of a non-electrically conductive material.

An apparatus comprising a sleeve that comprises a tubular portion, a receiving portion, and a coupling portion. The tubular portion has an outer diameter that is substantially equal to an inner diameter of a flexible hose such that the tubular portion is capable of being inserted within the flexible hose. The receiving portion extends outward from the tubular portion to thereby define a channel between the receiving portion and the tubular portion for receiving an end portion of a flexible hose. The coupling portion is for coupling the sleeve, and thereby, the flexible hose, to a component.

A jet engine is provided which can efficiently pressurize fuel. A jet engine 2 includes a pump 110 that heats fuel, a heating conduit 120 that heats the pressurized fuel, a fuel turbine 130 that provides mechanical power to the pump, and an electric rotating machine 140. When a given condition is not satisfied, the electric rotating machine 140 provides mechanical power to the fuel turbine 130. When the given condition is satisfied, the fuel that has passed through the heating conduit 120 before combustion flows into the fuel turbine 130 to provide mechanical power to the fuel turbine 130.

This fuel calculation device comprises: a remaining fuel amount calculation unit that periodically calculates and stores an approximate value of the remaining fuel amount on the basis of the measurement value of the remaining fuel amount remaining in a fuel container, and the fuel flow rate of fuel supplied from the fuel container; a failure determination unit that determines whether a remaining fuel amount meter that outputs the measurement value of the remaining fuel amount has failed; and a display control unit that controls so as to display the measurement value of the remaining fuel amount when the remaining fuel amount meter has not failed, and to display the approximate value of the remaining fuel amount when the remaining fuel amount meter has failed.

An embodiment includes an apparatus that supports a user to make planning decisions of fuel efficiency of an aircraft versus time of arrival of the aircraft along a flight path. An embodiment of the apparatus accepts input data related to the aircraft. The input data may include (i) flight plan data that includes a flight path of the aircraft, (ii) state of the aircraft along the flight path, (iii) environmental data, and (iv) an aircraft performance model of the aircraft. The apparatus calculates aircraft performance and an objective function for a range of altitudes and speeds as a function of the input data. The apparatus causes a user interface to display aircraft performance contour boundaries and a vertical routing path that meets the objective function to provide graphical representations to support a user's planning decisions.

A tank vent tube for a deaerator tank system, comprising a tube body. The tube body can define a vent channel. The tube can include a relief hole defined through the tube body. The tube can include a venturi structure disposed in the vent channel of the tube body at least partially over the relief hole. The venturi structure can be configured to reduce pressure over the relief hole as a function of flow in the vent channel.

An aircraft motive flow line includes an outer tube made out of a first material and an inner tube extending longitudinally inside the outer tube. The inner tube is made out of a second material having a thermal conductivity coefficient lower than that of the first material. The first material has a strength coefficient greater than that of the second material. The inner tube is sized and held in position relative to the outer tube so as to define a gap between an exterior of the inner tube and an interior of the outer tube. A port fluidly connects an interior of the inner tube to the gap.