Abstract: A fiber preform is provided. The fiber preform may comprise a base including a fiber weave with a plurality of fibers oriented in three directions. A plurality of legs may extend a first height from the base and include a fiber weave with the plurality of fibers oriented in three directions. A fiber reinforcement may be disposed proximate the legs with a second height equal to the first height. The fiber reinforcement may comprise a first ply and a second ply oriented orthogonal to the first ply in a plane parallel to the legs.

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: Aspects of the disclosure are directed to a system for an aircraft comprising: a titanium bottle section that includes at least two sections configured to house an engine, and at least one bifurcation panel coupled to the bottle section, wherein the at least one bifurcation panel includes a material that is different from titanium.

Abstract: A nacelle for an aircraft propulsion system includes a core cowl portion, a bifurcation portion and an extension portion. The core cowl portion extends about a centerline to the bifurcation portion. The bifurcation portion is connected to and extends radially between the core cowl portion and the extension portion. The extension portion projects out from the bifurcation portion and circumferentially extends over the core cowl portion. The extension portion includes an acoustic panel and a structural reinforcement. The acoustic panel includes a cellular core between a perforated face skin and a back skin, wherein the face skin is radially inboard of the back skin. The structural reinforcement is bonded to the back skin and structurally reinforces the acoustic panel.

Abstract: Aspects of the disclosure are directed to a panel configured for use on an aircraft nacelle, comprising: a first skin, a second skin, a first core portion coupled to the first skin and the second skin, a second core portion coupled to the first skin and the second skin, and an insert coupled to the first skin, the second skin, the first core portion, and the second core portion, the insert forming a corner fitting between the first core portion and the second core portion.

Abstract: Aspects of the disclosure are directed to a structure comprising: a plurality of cells, a first non-permeable insert in a first cell of the plurality of cells, the first insert configured to constrict, by at least a first threshold amount, a flow of fluid in the first cell such that: acoustic power over a frequency range is attenuated by the structure by at least a second threshold amount, and a resonant frequency associated with the structure is shifted by at least a third threshold amount.

Abstract: A nacelle may include a noise suppressing structure. The noise suppressing structure may utilize a noise suppressing cells situated between a perforated layer of material and a non-perforated layer of material. The noise suppressing cells may have a first portion and a second portion separated by a septum. The first portion may contact the septum at an obtuse angle and the second portion may contact the septum at a reflex angle.

Abstract: Aspects of the disclosure are directed to a structure comprising: a plurality of cells, a first non-permeable insert in a first cell of the plurality of cells, the first insert configured to constrict, by at least a first threshold amount, a flow of fluid in the first cell such that: acoustic power over a frequency range is attenuated by the structure by at least a second threshold amount, and a resonant frequency associated with the structure is shifted by at least a third threshold amount.

Abstract: Manufacturing processes is provided for forming a thrust reverser cascade an aircraft propulsion system. The thrust reverser cascade may include an array of vanes connected to and extending laterally between longitudinally extending first and second strongback rails. In one of the processes, the forming of the thrust reverser cascade includes additive manufacturing the first strongback rail and/or at least one of the vanes. This first strongback rail may include a length of fiber which extends more than eighty-five percent of a longitudinal length of the first strongback rail.

Abstract: A hybrid beam for support of a nacelle panel of a jet engine is disclosed. The beam is comprised of a first longitudinal composite panel and a second longitudinal composite panel, wherein the first longitudinal composite panel is integrally affixed to the second longitudinal composite panel along a longitudinal edge. The composite panels form a composite beam structure that is substantially open with a cross-section that is generally “L-shaped”. A plurality of hinge stations are affixed to a first side of the first longitudinal composite panel and at least one track guide is disposed on a second side of the first longitudinal composite panel. The track guides receive a head portion of a slider that is fixed to the translating jet engine nacelle panel. Each hinge station further comprises a bushing for defining a center of rotation for the jet engine nacelle panel relative to the beam.

Abstract: A nacelle may include a noise suppressing structure. The noise suppressing structure may utilize a noise suppressing cells situated between a perforated layer of material and a non-perforated layer of material. The noise suppressing cells may have a first portion and a second portion separated by a septum. The first portion may contact the septum at an obtuse angle and the second portion may contact the septum at a reflex angle.

Abstract: A fiber preform is provided. The fiber preform may comprise a base including a fiber weave with a plurality of fibers oriented in three directions. A plurality of legs may extend a first height from the base and include a fiber weave with the plurality of fibers oriented in three directions. A fiber reinforcement may be disposed proximate the legs with a second height equal to the first height. The fiber reinforcement may comprise a first ply and a second ply oriented orthogonal to the first ply in a plane parallel to the legs.

Abstract: An acoustic liner has a honeycomb layer disposed between a first panel and a permeable panel and includes a plurality of serpentine walls spaced apart from one-another. Adjacent serpentine walls outline in-part a first region carried by the first panel and an opposing second region carried by the permeable panel. The first and second regions are offset such that a centerline distance extending between the regions and centered between adjacent walls is greater than a distance measured directly between the panels, enabling the design of thinner acoustic liners. The regions and adjacent walls further define a cell having a constricted portion communicating between an end portion and an entry portion such that the constricted portion creates a frequency shift.

Abstract: Aspects of the disclosure are directed to a system configured to selectively hold open an aircraft engine cowl, comprising: a rod, a slider coupled to the rod, a track coupled to the slider, a latch coupled to the track. Aspects of the disclosure are directed to a nacelle system of an aircraft, comprising: an engine case, a bracket attached to the engine case or a cowl, a rod coupled to the bracket via a bearing, a clevis coupled to the rod, a slider coupled to the clevis, a track coupled to the slider and to the engine case or the cowl, and a latch coupled to the track that is configured to control a translation of the slider along the track based on a state of the cowl.

Abstract: An acoustic liner has a honeycomb layer disposed between a first panel and a permeable panel and includes a plurality of serpentine walls spaced apart from one-another. Adjacent serpentine walls outline in-part a first region carried by the first panel and an opposing second region carried by the permeable panel. The first and second regions are offset such that a centerline distance extending between the regions and centered between adjacent walls is greater than a distance measured directly between the panels, enabling the design of thinner acoustic liners. The regions and adjacent walls further define a cell having a constricted portion communicating between an end portion and an entry portion such that the constricted portion creates a frequency shift.

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: 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: Aspects of the disclosure are directed to a system for an aircraft comprising: a titanium bottle section that includes at least two sections configured to house an engine, and at least one bifurcation panel coupled to the bottle section, wherein the at least one bifurcation panel includes a material that is different from titanium.

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: A hybrid beam for support of a nacelle panel of a jet engine is disclosed. The beam is comprised of a first longitudinal composite panel and a second longitudinal composite panel, wherein the first longitudinal composite panel is integrally affixed to the second longitudinal composite panel along a longitudinal edge. The composite panels form a composite beam structure that is substantially open with a cross-section that is generally “L-shaped”. A plurality of hinge stations are affixed to a first side of the first longitudinal composite panel and at least one track guide is disposed on a second side of the first longitudinal composite panel. The track guides receive a head portion of a slider that is fixed to the translating jet engine nacelle panel. Each hinge station further comprises a bushing for defining a center of rotation for the jet engine nacelle panel relative to the beam.