Abstract: A manufacturing method is provided which utilizes a laser system. During an embodiment of this method, an object is arranged relative to a head of the laser system. A pattern of holes are formed in the object by ablating the object with a plurality of laser beams which are directed from the head.

Abstract: A nacelle may comprise an acoustic panel in an inner fixed structure. The acoustic panel may comprise a top sheet having elongated perforations oriented in a circumferential direction. A low drag liner may be coupled to the top sheet. The orientation of the elongated perforations may result in a greater hoop strength for the top sheet as compared to a top sheet of similar thickness and percent open area having circular perforations.

Abstract: Acoustic panels and methods for manufacturing acoustic panels are provided. In one such method, a core structure is provided between and bonded to a top skin and a septum. A plurality of perforations are formed in the top skin using an energy beam device. A plurality of perforations are formed in the septum through the top skin holes using the energy beam device. A plurality of cavities in the core structure fluidly couple at least some of the perforations in the top skin with at least some of the perforations in the septum.

Abstract: A process is provided for forming a plurality of apertures in a fiber-reinforced composite object using a laser. The apertures include at least a first aperture and a second aperture. During the process, a scanner head of the laser is operated from a location to selectively scan a laser beam over the object to form a first portion of the first aperture and to form a first portion of the second aperture. The scanner head is also operated from the location to selectively scan the laser beam over the object to form a second portion of the first aperture and to fowl a second portion of the second aperture.

Abstract: An acoustic liner that may be for a turbofan engine includes a first panel that may be non-permeable and a permeable panel spaced from the first panel. A non-permeable wall located between the first panel and the permeable panel faces in a first direction away from the first panel and a non-permeable wall, also between the panels, faces in a second direction away from the first panel and traversing the first direction. The liner may further include a plurality of sidewalls spaced from one-another, extending between the panels, and through the walls.

Abstract: A nacelle is disclosed. The nacelle may include an inner fixed structure (“IFS”) comprising a first half, the first half comprising a central barrel portion, wherein the first half includes a first member that extends radially outward from the central barrel portion and a second member that extends radially outward from the central barrel portion radially opposite the first member, a first support structure overlaid by a first composite material that extends axially along a confluence between the central barrel portion and the first member, the first support structure configured to contact a second half comprising a second central barrel portion, and a second support structure overlaid by a second composite material that extends axially along the confluence between the central barrel and the second member, the second support structure configured to contact the second half.

Abstract: An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.

Abstract: A nacelle may comprise a noise suppressing structure. The noise suppressing structure may comprise a plurality of noise suppressing cells situated between a perforated layer of material and a non-perforated layer of material. The plurality of noise suppressing cells may contact the perforated layer of material and the non-perforated layer of material at an acute angle (e.g., between twenty and seventy-five degrees) such that the plurality of noise suppressing cells are non-orthogonal to the perforated layer of material and the non-perforated layer of material. Further, each of the plurality of noise suppressing cells may comprise a hexagonal cross-sectional profile. Further still, the noise suppressing structure may comprise a support structure comprising a plurality of support members, wherein the plurality of noise suppressing cells are situated within the support structure.

Abstract: Surface films, paints, or primers can be used in preparing aircraft structural composites that may be exposed to lightning strikes. Methods for making and using these films, paints or primers are also disclosed. The surface film can include a thermoset resin or polymer, e.g., an epoxy resin and/or a thermoplastic polymer, which can be cured, bonded, or painted on the composite structure. Low-density electrically conductive materials are disclosed, such as carbon nanofiber, copper powder, metal coated microspheres, metal-coated carbon nanotubes, single wall carbon nanotubes, graphite nanoplatelets and the like, that can be uniformly dispersed throughout or on the film. Low density conductive materials can include metal screens, optionally in combination with carbon nanofibers.

Abstract: A panel for a nacelle structure that surrounds a jet engine core includes a longitudinally extending, generally semicircular center region, an upper bifurcation region, a lower bifurcation region, a hinge beam region extending from the upper bifurcation region and configured to receive an upper thrust reverser track guide, and a latch beam region extending from the lower bifurcation region and configured to receive a lower thrust reverser track guide. A bypass duct is formed in a space between the panel and the nacelle structure. A hinge beam structure and latch beam structure are integrally formed with the panel. An inner skin layer extends continuously across a bond panel surface generally facing the engine core and an outer skin layer extends continuously across a bond panel surface generally facing the bypass duct, the inner and outer skin layers extending across the center region, upper and lower bifurcation regions, hinge beam region, and latch beam region.

Abstract: An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.

Abstract: A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.

Abstract: A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.

Abstract: A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.

Abstract: An acoustic inner barrel for an aircraft engine nacelle inlet is constructed from a composite material and is formed as a single, 360-degree annular segment. The barrel includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially from the inner skin to the outer skin.

Abstract: An acoustic inner barrel for an aircraft engine nacelle inlet is constructed from a composite material and is formed as a single, 360-degree annular segment. The barrel includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially from the inner skin to the outer skin.

Abstract: Surface films, paints, or primers can be used in preparing aircraft structural composites that may be exposed to lightning strikes. Methods for making and using these films, paints or primers are also disclosed. The surface film can include a thermoset resin or polymer, e.g., an epoxy resin and/or a thermoplastic polymer, which can be cured, bonded, or painted on the composite structure. Low-density electrically conductive materials are disclosed, such as carbon nanofiber, copper powder, metal coated microspheres, metal-coated carbon nanotubes, single wall carbon nanotubes, graphite nanoplatelets and the like, that can be uniformly dispersed throughout or on the film. Low density conductive materials can include metal screens, optionally in combination with carbon nanofibers.

Abstract: A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.