Rohr Patente

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A method is provided during which a preform is provided that includes an electric heater (44) and thermoplastic material. The preform is consolidated to provide an aircraft component (22). The consolidating includes heating the thermoplastic material using the electric heater (44). The electric heater (44) is embedded within the thermoplastic material of the aircraft component (22). The electric heater (44) is configured as a part of a thermal anti-icing system (24) for melting and/or preventing ice accumulation on an exterior surface (28) of the aircraft component (22).

A method is provided during which a composite preform is provided that includes an electric heater (44), fiber-reinforcement and thermoset material. The composite preform is consolidated to provide a composite aircraft component (22). The consolidating includes heating the thermoset material using the electric heater (44) to cure the thermoset material. The electric heater (44) and the fiber-reinforcement are embedded within the cured thermoset material. The electric heater (44) is configured as a part of a thermal anti-icing system (24) for melting and/or preventing ice accumulation on an exterior surface (28) of the composite aircraft component (22).

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An assembly is provided for induction welding. This assembly utilizes a heat shield (e.g., a mica heat shield) (322) with a recess (324). An induction welding coil (312) may be disposed within this heat shield recess (324) during induction welding operations. The wall thickness of the heat shield (322) within the recess (324) may be reduced to enhance heat transfer to a workpiece during induction welding operations. The heat shield (322) may be coated with a ceramic coating (809) to enhance the heat shield's heat resistance and reduce heat shield flaking at the recess during induction welding operations.

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A method of manufacturing a thermoplastic panel may comprise: laying up a panel preform (310) within a consolidation assembly (400), the panel preform (310) comprising a plurality of plies of material comprising thermoplastic resin and fiber; generating, via a hot bond unit, a vacuum environment within the consolidation assembly (400); and heating, via the hot bond unit and through a heated blanket (450) within the consolidation assembly (400), the panel preform (310).

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<div notation="docdba" type="abstract" xml:base="/api/emi/section/a9de3315-6fea-4ade-903c-ddbc3b92bbc5/image" xml:lang="en"><p>A thrust reverser system of a nacelle is provided. The thrust reverser system may include a pressure shell (243), a blocker door (220), and a drag link (400). The blocker door (220) may be pivotably coupled to the pressure shell (243). The drag link (400) may include a first segment (410) pivotably coupled to a second segment (430) and a third segment (450) pivotably coupled to the second segment (430) and the blocker door (220).</p></div>

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A thrust reverser assembly (16) may comprise a sleeve (112) including an inner sleeve portion (120) and an outer sleeve portion (122). A plurality of guide rails may be coupled to a radially outward surface of the inner sleeve portion. A plurality of blocker doors (150) may be slidably coupled to the plurality of guide rails. The plurality of blocker doors may be located between the inner sleeve portion and the outer sleeve portion.

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A thermoforming method includes heating a thermoplastic panel (210, 410) to a forming temperature, and compressing the thermoplastic panel between a first tool (230) and a second tool (232), wherein the thermoplastic panel is bent about a first axis (290) extending along a first direction with respect to the thermoplastic panel in response to being compressed between the first tool and the second tool. The thermoplastic panel may then be cooled to a hardened temperature and disposed between a third tool (240) and a fourth tool (242). The method further includes heating the thermoplastic panel to the forming temperature, and compressing the thermoplastic panel between the third tool and the fourth tool, wherein the thermoplastic panel is bent about a second axis (292) extending along a second direction with respect to the thermoplastic panel in response to being compressed between the third tool and the fourth tool.

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A piccolo tube (152) for an anti-icing system may comprise an annular tube (156) and a plurality of openings (154) formed along a circumference of the annular tube. The annular tube may comprise a first cross-sectional diameter (D1) at an inlet point (160) and a second cross-sectional diameter (D2) at a distal point (162). The second cross-sectional diameter is less than first cross-sectional diameter. The distal point may be 180° from the inlet point.

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An aerospace component (100) may comprise a fiber reinforced composite material (102). The fiber reinforced composite material (102) includes a plurality of fiber layers and a carbon matrix (106) surrounding the plurality of fiber layers. A plurality of ceramic particles (108) is dispersed in the carbon matrix (106). A first fiber layer of the plurality of fiber layers may include a carbon fiber (104a), and a second fiber layer of the plurality of fiber layers may include a non-carbon fiber (104b). A hardness of the non-carbon fiber (104b) is greater than a hardness of carbon fiber (104a).

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An aircraft assembly (20) includes an aircraft control surface (24) having a first skin (50), a second skin (52) and a support structure laterally between and connected to the first skin (50) and the second skin (52). The support structure includes a spar (60C), a first stiffener and a second stiffener. The spar extends spanwise within the aircraft control surface (24). The first stiffener extends longitudinally within the aircraft control surface to the spar. The second stiffener extends longitudinally within the aircraft control surface (24) to the spar (60C). An actuator receptacle projects longitudinally into the aircraft control surface (24) from a base (42) of the aircraft control surface (24) to the spar. The actuator receptacle extends spanwise within the aircraft control surface (24) between the first stiffener and the second stiffener.

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