Abstract: A system is provided for translating sections of an icing wind tunnel to expand a size range of water droplets. The system includes: a set of actuators coupled to a set of sections of the icing wind tunnel; and a controller coupled to the set of actuators, wherein the controller is configured to: receive data relating to a water droplet generated within the icing wind tunnel; determine a directional impact on a model within the icing wind tunnel based upon the data relating to the water droplet; and adjust at least one of the set of sections of the icing wind tunnel in at least one of an up or a down direction in a subsequent test.

Abstract: 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.

Abstract: 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.

Abstract: A de-icing assembly for a surface of an aircraft includes a carcass, seams, inflation passages, a manifold, and a reinforcement stitchline. The carcass includes a first layer, a second layer, and a carcass centerline. The seams are sewn into the carcass and join the first and second layers of the carcass together. The inflation passages are formed by the seams and are disposed between the first and second layers of the carcass. The manifold includes a width and a manifold centerline oriented approximately perpendicular to the carcass centerline and is fluidly connected to and is disposed beneath the carcass. The first reinforcement stitchline is sewn into the carcass adjacent to one of the plurality of seams and is disposed at a location on the carcass overlapping with the manifold. The first reinforcement stitchline is disposed approximately perpendicular to the manifold centerline and extends across the width of the manifold.

Abstract: A de-icing assembly for a surface of an aircraft includes a carcass with a first layer and a second layer, a plurality of seams sewn into the carcass, and a bonded region. The plurality of seams join the first and second layers of the carcass together. Each of the plurality of seams comprises two or more stitchlines. The bonded region is disposed between the two or more stitchlines and seals a portion of the first layer of the carcass to a portion of the second layer of the carcass.

Abstract: A de-icing assembly for a surface of an aircraft includes a carcass with a first layer and a second layer, a plurality of seams sewn into the carcass, and a bonded region. The plurality of seams join the first and second layers of the carcass together. Each of the plurality of seams comprises two or more stitchlines. The bonded region is disposed between the two or more stitchlines and seals a portion of the first layer of the carcass to a portion of the second layer of the carcass.

Abstract: A de-icing assembly for a surface of an aircraft includes a carcass, seams, inflation passages, a manifold, and a reinforcement stitchline. The carcass includes a first layer, a second layer, and a carcass centerline. The seams are sewn into the carcass and join the first and second layers of the carcass together. The inflation passages are formed by the seams and are disposed between the first and second layers of the carcass. The manifold includes a width and a manifold centerline oriented approximately perpendicular to the carcass centerline and is fluidly connected to and is disposed beneath the carcass. The first reinforcement stitchline is sewn into the carcass adjacent to one of the plurality of seams and is disposed at a location on the carcass overlapping with the manifold. The first reinforcement stitchline is disposed approximately perpendicular to the manifold centerline and extends across the width of the manifold.

Abstract: A ram air turbine movable between a stowed position and a deployed position is provided including a rotatable hub assembly. A hub face is arranged at a first end of the rotatable hub assembly. The hub face has a non-planar configuration such that a limited portion of a surface area of the hub face is arranged within a plane oriented perpendicular to a direction of travel of an airflow upstream from the hub face when the ram air turbine is in a deployed position.

Abstract: A valve includes a body with an inlet at a first end of the body, and an outlet at a second end of the body. A first electrically resistive heating element is located in the inlet and heats a first fluid source to a temperature above 0 degrees C. A second electrically resistive heating element is located in the outlet and heats a second fluid source to a temperature above 0 degrees C.

Abstract: 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.

Abstract: A method of manufacturing a de-icer assembly includes positioning a first welded-material layer and a second welded-material layer between a die and a die base of a die-based welding system, wherein at least one of the die and the die base includes a welded-portion pattern configured to weld the first welded-material layer to the second welded-material layer in the 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, pressing the first welded-material layer and the second welded-material layer together between the die and die base, and applying high energy to the die-based welding system using a high energy source such that the first welded-material layer and the second welded-material layer are welded together at the areas in the shape of the welded-portion pattern to form a welded de-icer assembly.

Abstract: 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.

Abstract: A valve includes a body with an inlet at a first end of the body, and an outlet at a second end of the body. A first electrically resistive heating element is located in the inlet and heats a first fluid source to a temperature above 0 degrees C. A second electrically resistive heating element is located in the outlet and heats a second fluid source to a temperature above 0 degrees C.

Abstract: A ram air turbine movable between a stowed position and a deployed position is provided including a rotatable hub assembly. A hub face is arranged at a first end of the rotatable hub assembly. The hub face has a non-planar configuration such that a limited portion of a surface area of the hub face is arranged within a plane oriented perpendicular to a direction of travel of an airflow upstream from the hub face when the ram air turbine is in a deployed position.

Abstract: An ice protection system (20) comprises a deicer pad (30) with a first chamber (40) and a second chamber (50) bordering the first chamber (40). The inflation channels (41) in the first chamber (40) do not communicate with the inflation channels (51) in the second chamber (50). An inflation-fluid source (80) is plumbed to a connection port (43) and a connection port (53), both of which are located on an inboard providence of the deicer pad (30).

Abstract: An electrical resistance heating element of the sort suitable for use in de-icing an aircraft surface includes a foil patterned with a plurality of holes. The holes are in a first patterned region that extends in a first direction from a first end to an opposite second end. The holes define multiple electrical paths between the two ends. The holes, which may vary in size, are configured and dimensioned such that the multiple electrical paths in areas away from lateral edges of said first patterned region are all non-parallel to the first direction. In other words, the electrical paths do not follow a straight line from the first and second ends, but rather must wend their way around the overlapping holes.

Abstract: A pneumatic deicing system includes a deicer assembly comprised of an outer layer, an inner ply, and a plurality of inflatable members provided therebetween. The deicer assembly is disposed directly on top of and bonded to an airfoil. The deicer assembly is inflated through an inflation port. Fluid is drained from the deicer assembly through a drain valve.

Abstract: A pneumatic deicing system for deicing an airfoil includes a flexible deicing member having inflatable tube-like passages provided therein for being inflated with a pressurized fluid, wherein the deicing member is bonded to a shell having a snap type connector for mating with another connector either on the airfoil or integrated into another part of the shell. An air connector extends through the shell and is utilized for putting the deicing member in fluid connection with the fluid source. Radar absorptive material may be disposed between the shell and the deicing member for reducing the radar cross section of the airfoil.

Abstract: A pneumatic deicing distribution valve 10 includes a body 12, a cap assembly 14 and a rotary member 30 contained therein. Rotary member 30 selectively connects an input port 18 with a plurality of output ports 20 for selectively pressurizing one of a number of deicing apparatuses. A vacuum port 24 places all output ports not being pressurized under vacuum.

Abstract: A pneumatic deicer assembly 32 for attachment to an airfoil includes a pair of plies 52, 54 which are stitched together with a zig-zag stitch line which periodically crosses over the airfoil leading edge.