Pneumatic air systems for use onboard aircraft include a compressor configured to receive air from an air supply and increase a pressure of said received air to generate compressed air, a heat exchanger configured to receive the compressed air as a first working fluid and a treating air as a second working fluid, the heat exchanger configured to convert the compressed air to compressed and temperature treated air, one or more aircraft systems configured to receive the compressed and temperature treated air, and a surge prevention circuit arranged to prevent surge of air at the compressor, wherein the surge prevention circuit comprises a mechanical valve that is actuated based on a detected pressure within a sense line operably coupled to the mechanical valve.

An air supply system for a pneumatic de-icing assembly for de-icing surfaces of an aircraft, the aircraft comprising an air-conditioning system supplied by at least one first air compressor connected to a device for drawing in air outside the aircraft, the pneumatic de-icing assembly comprising an air supply inlet connected to an outlet of the first air compressor or to an outlet of the air-conditioning system. Thus, it is possible to supply air to a pneumatic de-icing system of an airplane equipped with electric motors or of what is referred to as “bleedless” type.

An ice protection system adapted to protect at least one ice-susceptible flight surface of an aircraft includes a mechanical ice protection device attached to the flight surface. A controller controls a power source that causes the mechanical ice protection device to change in shape and, thereby, change an aerodynamic characteristic of the flight surface. This change in shape happens only when the current thickness of ice on the surface exceeds a minimum thickness.

A de-icing assembly for a surface of an aircraft includes: a carcass with a first layer, a second layer, and a carcass centerline and a plurality of seams sewn into the carcass, wherein the plurality of seams join the first and second layers of the carcass together. The assembly includes a plurality of inflation passages formed by the plurality of seams and disposed between the first and second layers of the carcass. The system also includes a manifold fluidly connected to and disposed beneath the carcass, the manifold comprising a width and a manifold centerline oriented approximately perpendicular or parallel to the carcass centerline. The seams are sown by a stitchline formed of carbon nanotube yarn

A de-icer is provided and includes first and second structural layers that each include centerline and a non-inflatable edge angled with respect to the centerline, edge sealing material disposed to adhere the first and second structural layers together to form a non-inflatable edge area extending along at least the non-inflatable edge and surrounding a central area and stitching. The stitching is disposed to stitch the first and second structural layers together in the central area to form tubes. The tubes include an outermost tube which is closest to and parallel with the non-inflatable edge.

A structure adapted to traverse a fluid environment exerting an ambient fluid pressure is provided. The structure includes an elongate body extending from a root to a wingtip and encapsulating at least one interior volume containing an interior fluid exerting an interior fluid pressure that is different from the ambient fluid pressure. A method of retrofitting a structure adapted to traverse a fluid environment exerting an ambient fluid pressure, the structure comprising an elongate body extending from a root to a wingtip and having at least one interior volume is also provided. The method includes sealing the elongate body to encapsulate the at least one interior volume containing an interior fluid; associating at least one valve with the at least one interior volume; and modifying interior fluid content via the at least one valve to produce an interior fluid pressure that is different from the ambient fluid pressure.

Examples described herein provide a computer-implemented method that includes receiving static data about an aircraft. The method further includes receiving dynamic data about flight conditions for a flight of the aircraft. The method further includes determining, based on the static data and the dynamic data, an amount of air pressure and a volumetric air flow to apply from an electric pump to a deicing device. The method further includes controlling the electric pump to cause the electric pump to apply the amount of air pressure and the volumetric air flow to the deicing device.

A de-icing assembly includes an aircraft with an airfoil. A de-icer is disposed on a leading edge of the airfoil. A tab extends from the de-icer in an aft direction from an aft edge of the de-icer. The de-icer and the tab are adhesively attached onto an outer skin of the airfoil. A supercooled large droplet sensor is built into the tab. The supercooled large droplet sensor is positioned in a location aft of the aft edge of the de-icer.

A method of manufacturing a de-icer assembly includes disposing a first welded-material layer and a second welded-material layer beneath a horn of a horn-based welding system, controlling the horn to move along a welded-portion pattern configured to weld the first welded-material layer to the second welded-material layer in the pattern of the welded-portion pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer, and applying high-frequency energy to the first welded-material layer and a second welded-material layer using the horn such that the first welded-material layer and the second welded-material layer are welded together at areas in the shape of the welded-portion pattern to form a welded de-icer assembly.

A die-welding system for a de-icer assembly includes a die, a die base, a high energy source, and a de-icer assembly. The de-icer assembly includes a first welded-material layer and a second welded-material layer. At least one of the die and the die base includes a welded-portion pattern thereon configured to weld the first welded-material layer to the second welded-material layer in the pattern of the welded-portion pattern such that inflatable portions are formed within the welded-portion pattern formed in the de-icer assembly between non-welded sections of the first welded-material layer and the second welded-material layer.