Abstract: A first thermoplastic component and a second thermoplastic component including a first joint portion and a second joint portion, respectively, are provided. A least a portion of a surface area of each of the first and second joint portions include a respective first and second mating surface. The first and second mating surfaces of the respective first and second joint portions are positioned in contact with one another. The first and second joint portions are fusion joined. Fusion joining the first and second joint portions forms a fused unitary portion of the first and second thermoplastic components.

Abstract: A manufacturing method is disclosed herein. The method includes arranging a preform with a plurality of clamping assemblies, the plurality of clamping assemblies disposed along ends of the preform; and forming the preform into a shaped body, the forming including: incrementally tensioning the preform around a surface of an inner mold line using the plurality of clamping assemblies; and drawing the preform into a set of forming beads of the inner mold line.

Abstract: 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.

Abstract: An arrangement for forming an annular component includes a small diameter clamp for securely retaining a first holding surface of a small diameter end of a preform, a large diameter clamp for securely retaining a second holding surface of a large diameter end of the preform, and a punch having an external surface contour shaped to correspond to a shape of a profile of the annular component. The small diameter clamp and/or the large diameter clamp is configured to clamp the respective small and/or large holding surface, respectively, at an angle other than a slant angle of a main frusto-conical portion of the preform.

Abstract: A bullnose ramp is disclosed. In various embodiments, the bullnose ramp includes a forward portion, the forward portion characterized by a first profile; an aft portion, the aft portion characterized by a second profile; and a transition portion positioned proximate an intersection between the forward portion and the aft portion, the transition portion defining a change in slope between the first profile and the second profile.

Abstract: An acoustic system for an Urban Air Mobility (UAM) vehicle may comprise a first shield configured to be disposed around a rotor of the UAM vehicle, the first shield having an annular shape, the first shield configured to be disposed radially outward from a blade tip of a rotary blade, the first shield configured to redirect sound waves from a substantially radial direction to a second direction, the second direction being orthogonal to the radial direction.

Abstract: A method for forming a fiber-reinforced thermoplastic hollow structure may comprise: abutting a first surface of a first flange of a shell and a second surface of a second flange of the shell with a mating component; disposing an end block laterally adjacent to the shell; applying a first load to a sidewall of the shell; applying a second load to the second flange of the shell; and vibrating one of the shell or the mating component while keeping a non-vibrating component stationary, the non-vibrating component including one of the shell or the mating component.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a forward thrust duct and a thrust reverser system. The thrust reverser system includes a thrust reverser duct, a bullnose ramp and a plurality of protrusions. The bullnose ramp is adapted to provide a transition from the forward thrust duct to the thrust reverser duct when the thrust reverser system is in a deployed configuration. The protrusions are bonded or formed integral with the bullnose ramp. Each of the protrusions is adapted to interact with boundary layer fluid flowing along the bullnose ramp from the forward thrust duct into the thrust reverser duct when the thrust reverser system is in a deployed configuration.

Abstract: A control surface for an aircraft comprise a first skin, a second skin bonded to the first skin, and a stiffening structure located between the first skin and the second skin. The stiffening structure may be formed by forming a plurality of fiber-mandrel sections, stacking the plurality of fiber-mandrel sections to form a fiber-mandrel assembly, and depositing an outer fiber ply around a perimeter of the fiber-mandrel assembly. The control surface may be formed by forming a part layup over a first mold surface, contacting the part layup with a second mold surface, and curing the part layup. Forming the part layup over a first mold surface may include locating a first fiber ply over the first mold surface, locating a plurality stiffening structure assemblies over the first fiber ply, and locating a second fiber ply over the plurality stiffening structure assemblies.

Abstract: A latch mechanism is disclosed. In various embodiments, the latch mechanism includes a T-bolt body and a T-bolt comprising a longitudinal rod extending in a longitudinal direction from the T-bolt body and a transverse rod disposed at an end of the longitudinal rod. A safety keeper defining a load slot may be configured to receive the transverse rod whereby the T-bolt is configured to secure the T-bolt body with respect to the safety keeper.

Abstract: A method for dehumidifying a perforated acoustic skin includes disposing a sheet of material over a perforated acoustic skin, sealing a periphery of the sheet of material to the perforated acoustic skin to form a cavity between the sheet of material and the perforated acoustic skin, disposing at least one dehumidifier in fluid communication with the cavity, and activating the dehumidifier to remove moist air from a core of the perforated acoustic skin. The dehumidifier(s) may be mounted to the sheet of material.

Abstract: A manufacturing method is provided during which a plurality of first apertures are formed in a first plate to provide an apertured first plate. A plurality of second apertures are formed in a second plate to provide an apertured second plate. The apertured first plate and the apertured second plate are bonded to a base sheet to form a structure. The base sheet is bent to form a bend in the structure between the apertured first plate and the apertured second plate.

Abstract: A method for forming a fiber-reinforced thermoplastic control surface may comprise: stacking plies of thermoplastic composite sheets to a first desired thickness to form a first skin; stacking plies of thermoplastic composite sheets to a second desired thickness to form a second skin; forming the first skin in a first contour; forming the second skin in a second contour; forming a stiffening member including a thermoplastic resin, the stiffening member including a shape having a plurality of peaks and troughs; assembling the stiffening member between the first skin and the second skin; and joining the stiffening member to the first skin and the second skin.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a first actuator, a second actuator and a linkage system. The linkage system is configured to transfer torque between the first actuator and the second actuator. The linkage system includes a first linkage shaft, a second linkage shaft and a gearbox. The first linkage shaft has a first centerline. The second linkage shaft has a second centerline offset from the first centerline. The gearbox is coupled to and is between the first linkage shaft and the second linkage shaft.

Abstract: A latch handle arrangement includes a latch handle body and a removable insert. The latch handle body comprises a first sidewall, a second sidewall, and a transverse wall extending from the first sidewall to the second sidewall. The latch handle body further comprises one or more apertures disposed in the latch handle body. The removable insert is configured to be coupled to the latch handle body. The removable insert comprises an insert body and one or more bosses protruding from the insert body into the respective apertures disposed in the latch handle body, wherein the boss(es) are visible from an external surface of the latch handle body.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a variable area inlet. The variable area inlet includes a moveable structure configured to move axially along an axial centerline between a first position and a second position. The variable area inlet is configured to open an airflow inlet passage into the aircraft propulsion system when the movable structure is in the first position. The variable area inlet is configured to close the airflow inlet passage when the movable structure is in the second position. The airflow inlet passage includes an inlet. The inlet extends axially along the axial centerline from a first end to a second end. A distance from the first end to the second end changes as the inlet extends laterally between a first side and a second side.

Abstract: A variable area nozzle assembly for a gas turbine engine includes a fixed structure surrounding an exhaust duct extending along a nozzle centerline. The fixed structure includes an upper side and a lower side opposite the upper side. The variable area nozzle assembly further includes a nozzle disposed about the nozzle centerline. The nozzle includes a nozzle throat cross-sectional area and a nozzle outlet cross-sectional area downstream of the nozzle throat cross-sectional area. The nozzle includes an upper panel and a lower panel. The upper panel includes an upper downstream end and the lower panel including a lower downstream end. The upper downstream end and the lower downstream end define a portion of the nozzle throat cross-sectional area. The variable area nozzle assembly further includes a nozzle actuation system including an upper shaft connected to the upper panel and a lower shaft connected to the lower panel.

Abstract: An induction welding system includes a first gantry, a second gantry, and a support structure. The first gantry includes a first frame and a first plurality of trunks. The first plurality of trunks defines a first curved inner support surface of the first gantry. The first curved inner support surface has a first curvature geometry. The second gantry includes a second frame and a second plurality of trunks. The second plurality of trunks defines a second curved inner support surface of the second gantry. The second curved inner support surface has a second curvature geometry which is different than the first curvature geometry. The support structure includes at least one tooling member defining a curved outer support surface of the support structure. The support structure is longitudinally moveable relative to the first gantry and the second gantry.

Abstract: A system for mounting a gas turbine engine to a pylon and for detecting a failure within the system, the gas turbine engine comprising a first case, is disclosed. In various embodiments, the system includes a first mount connecting the first case to the pylon; and a first sensor configured to detect a first relative motion between the first case and the first mount.

Abstract: An inlet cowl may comprise: a forward bulkhead; an aft bulkhead spaced apart axially aft of the forward bulkhead; an annular structure having a radially inner wall spaced apart from a radially outer wall; a fluid conduit extending axially through an aft plenum defined axially between the aft bulkhead and the forward bulkhead, the aft plenum defined radially between the radially inner wall and the radially outer wall; and an over-temperature indication assembly coupled to at least one of the radially outer wall and the aft bulkhead, the over-temperature indication assembly configured to transition from a retracted state to a deployed state in response to a portion of the over-temperature indication assembly exceeding a temperature threshold.