Rohr Patente

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Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

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.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

An acoustic liner includes a first face sheet, a second face sheet spaced from the first face sheet, and a plurality of sidewalls extending between the first face sheet and the second face sheet. The plurality of sidewalls defines a plurality of cells. Each cell of the plurality of cells defines a cavity between the first face sheet and the second face sheet. A bulk absorber is disposed within at least one cell of the plurality of cells. The bulk absorber further defines the cavity of the at least one cell of the plurality of cells. The first face sheet defines a plurality of apertures extending through a thickness of the first face sheet. Each aperture of the plurality of apertures is aligned with a respective cell of the plurality of cells.

A nacelle inlet (102) may comprise a lip skin (124) and a bulkhead (130, 156) mounted to the lip skin (124). The lip skin (124) may define an orifice. The bulkhead (130, 156) may comprise a forward face (136), a first flange (132, 134) extending axially from an outer circumference (140) of the forward face (136), and a ventilation groove (170) formed in the forward face (136). The ventilation groove (170) may be circumferentially aligned with the orifice.

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Systems and methods for lightning strike materials are disclosed. The material includes a carbon fiber tow (110) in a resin matrix and carbon nanotubes grown on the carbon fibers (112;122) within the carbon fiber tow (110). The carbon nanotubes cause the carbon fibers (112;122) to separate, decreasing a carbon tow fiber volume fraction of the tow (110). The growth of the carbon nanotubes may be controlled to select a tow fiber volume fraction of the tow (110) of less than 45%. The lightning strike material may transmit electricity to decrease damage to the composite structure in case of a lightning strike.

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An acoustic panel includes a first skin, a second skin and a cellular core (36) vertically between and connected to the first skin and the second skin. The cellular core (36) includes a plurality of cavities (48), a plurality of sidewalls (46) and a plurality of septums (50). Each of the plurality of cavities (48) extends vertically through the cellular core (36) between the first skin and the second skin. Each of the plurality of cavities (48) extends laterally within the cellular core (36) between a respective laterally adjacent pair of the plurality of sidewalls (46). Each of the plurality of septums (50) vertically divides a respective one of the plurality of cavities (48) into a set of fluidly coupled sub-cavities. A set of the plurality of septums (50) is formed by a ply of folded material. Each of the set of the plurality of septums (50) have a foursided polygonal shape when viewed in a plane (x-y) that is parallel to the first skin.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

A method for gathering flight load data for a gas turbine engine includes providing a plurality of blocker doors rotatably mounted to a translating sleeve and a plurality of blocker door islands, each blocker door island disposed between circumferentially adjacent blocker doors of the plurality of blocker doors and mounted to at least one mounting point of the translating sleeve, wherein a blocker door island of the plurality of blocker door islands is a data acquisition unit; and connecting the data acquisition unit to at least one sensor in communication with the translating sleeve.

A panel (20) for attenuating noise includes a core (26) having a first baffle (56), a second baffle (56), a first septum (58), a second septum (58) and a stiffener (50A). The core (26) forms first and second cavities (52A,B) vertically between a first skin (22) and a second skin (24), wherein the first and the second cavities (52A,B) are each fluidly coupled with perforations (34) in the first skin (22). The first cavity (52A) is formed laterally between the first baffle (56) and the second baffle (56) and has a first cross-sectional geometry. The first septum (58) is laterally between the first baffle (56) and the second baffle (56) and divides the first cavity (52A) into fluidly coupled sub-cavities. The second cavity (52B) is formed laterally between the second baffle (56) and the stiffener (50A) and has a second cross-sectional geometry that is at least approximately identical to the first cross-sectional geometry. The second septum (58) is laterally between the second baffle (56) and the stiffener (50A) and divides the second cavity (52B) into fluidly coupled sub-cavities.

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An apparatus for aircraft anti-icing includes a nozzle body (50, 750), at least one nozzle (34, 52, 54, 552, 56, 652, 752, 754, 756) extending from the nozzle body (50, 750), and at least one vane (511, 512, 513, 514) disposed in at least one of the nozzle(s), the at least one vane (511, 512, 513, 514) configured to impart rotational movement of a hot gas moving through the nozzle(s).

A manufacturing method is provided during which a plurality of first apertures (56) are formed in a first plate (102) to provide an apertured first plate (40). The apertured first plate (40) is configured from or otherwise includes first plate metal. A first sheet (38) is bonded to the apertured first plate (40) to form a first grid structure (22A). The first apertures (56) extend through the apertured first plate (40) to the first sheet (38). The first sheet (38) is configured from or otherwise includes first sheet metal.

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …

Zusammenfassung wird geladen …