Abstract: A variable area nozzle assembly includes a fixed structure surrounding an exhaust duct extending along a nozzle axis. The fixed structure defines an exhaust duct outlet of the exhaust duct. The fixed structure includes a first side beam and a second side beam. Each of the first side beam and the second side beam extend in a direction axially aft from the exhaust duct outlet. Each of an upper thrust reverser door and a lower thrust reverser door are pivotably mounted to the first side beam and the second side beam at a first axial position. An upper panel and a lower panel are pivotably mounted to the upper thrust reverser door and the lower thrust reverser door, respectively, at a second axial position located axially forward of the first axial position. The upper panel and the lower panel define a nozzle outlet cross-sectional area therebetween.

Abstract: An aerospace component may comprise a fiber reinforced composite material. The fiber reinforced composite material includes a plurality of fiber layers and a carbon matrix surrounding the plurality of fiber layers. A plurality of ceramic particles is dispersed in the carbon matrix. A first fiber layer of the plurality of fiber layers may include a carbon fiber, and a second fiber layer of the plurality of fiber layers may include a non-carbon fiber. A hardness of the non-carbon fiber is greater than a hardness of carbon fiber.

Abstract: A noise and vibration attenuation panel for a structure within a propulsion system includes a first plurality of unit cells and a first plurality of mass elements disposed within the first plurality of unit cells. The first plurality of unit cells include a first periodic structure having a first unit cell, a second unit cell, a third unit cell, and a fourth unit cell, each of the first unit cell, the second unit cell, the third unit cell and the fourth unit cell including a central body interconnected via a plurality of lateral tubes extending from the central body, the first periodic structure forming a first lateral layer of unit cells. The noise attenuation panel can simultaneously control acoustic waves or energy (i.e., via noise attenuation flow paths) and vibration (i.e., via the mass elements).

Abstract: A method of producing a cascade array and a cascade array is provided. The method includes: forming a plurality of strongbacks from a first thermoplastic material; forming a plurality of comb subassemblies, each said comb subassembly including one of the plurality of strongbacks and a plurality of vanes comprising a second thermoplastic material extending outwardly from the respective one of the plurality strongbacks; and attaching the plurality of comb subassemblies into a unitary structure to produce the cascade array.

Abstract: An aircraft anti-icing system is disclosed. A tube having a plurality of outlet ports is disposed within an interior of an outer housing in spaced relation to a closed end of this outer housing. The exterior of the outer housing includes a leading edge at its closed end. The tube is anchored relative to the outer housing by one or more brackets that extend from the tube to the outer housing. An open end of the outer housing may be closed by an aft wall that encloses the tube within an interior compartment of the outer housing.

Abstract: A method for forming a fiber-reinforced thermoplastic part may comprise the steps of locating a lightning strike protection layer on a mold surface of a mold tool, locating a thermoplastic layer over the mold tool, heating the thermoplastic layer to a pliable forming temperature, conforming the thermoplastic layer to a mold surface of the mold tool, and depositing a plurality of fiber strips over the thermoplastic layer.

Abstract: A method for forming a fiber reinforced thermoplastic part may comprise the steps of locating a thermoplastic material over a mold tool, heating the thermoplastic material to a pliable forming temperature, conforming the thermoplastic material to a mold surface of the mold tool, and depositing a plurality of fiber strips over the thermoplastic material.

Abstract: A pressure relief latch includes a housing configured to be mounted to a pressure relief door. A bolt is coupled to the housing about a first axis and is rotatable about the first axis between a first bolt position and a second bolt position. The bolt includes a bearing centered about a second axis. The bearing is configured to rotate about the second axis. A spring assembly includes a first assembly end mounted to the bearing and a second assembly end in rotational communication with the housing about a third axis. The spring assembly is rotatable about the second and third axes and further includes a spring extending between the first and second assembly ends. The bolt is configured to permit movement of the pressure relief door from the closed position to the open position as the bolt rotates from the first bolt position to the second bolt position.

Abstract: A powerplant can include a first prime mover configured to turn a propulsor, and a second prime mover operatively connected in parallel with the first prime mover to turn the propulsor together with or separately from the first prime mover. The powerplant can include a firewall disposed around at least one of the first prime mover or the second prime mover to create a first prime mover fire zone and a second prime mover fire zone separate from the first prime mover fire zone such that the first prime mover is protected against a second prime mover fire, and vice versa.

Abstract: Methods and apparatus' for induction welding a first workpiece to a second workpiece at a welding region may include a metallic strip. The metallic strip may be a mesh. The properties of the metallic strip, such as, for example, pore size, thickness, and density, may be configured to conduct heat uniformly across the welding region and prevent eddy current formation across a workpiece. The metallic strip may be embedded in a workpiece or may be fixed to an induction welding tool that acts on the welding region during induction welding. A removable polymer tape may be disposed between a workpiece and a metallic strip fixed to an induction welding tool. The workpieces may be thermoplastic composite structures and thermoplastic composite stiffeners in aircraft structures.

Abstract: Systems and methods for induction welding a stiffener to a thermoplastic composite structure using a removeable metal mask to reduce excess heat along the edges of the stiffener generated from an electromagnetic field of an induction welding tool.

Abstract: An assembly is provided for induction welding. This assembly utilizes a heat shield (e.g., a mica heat shield) with a recess. An induction welding coil may be disposed within this heat shield recess during induction welding operations. The wall thickness of the heat shield within the recess may be reduced to enhance heat transfer to a workpiece during induction welding operations. Members may engage the heat shield on opposite sides of the recess (and that have an increased wall thickness) to support both the heat shield and the workpiece during induction welding operations, during which a biasing force may be exerted on both the heat shield and workpiece.

Abstract: A method for forming a fiber-reinforced thermoplastic control surface includes forming first and second skins from a fiber-reinforced thermoplastic resin. The method further includes overmolding fiber-reinforced thermoplastic features onto the first skin and/or second skin, including stiffener structures, sidewalls, and/or hinges. The method further comprises welding or consolidating the first and second skins together, along with the associated internal features overmolded thereon to form a single-piece, stiffened, fiber-reinforced thermoplastic control surface.

Abstract: A thrust reverser assembly may comprise a cascade of vanes and a sleeve configured to translate relative to the cascade of vanes. The sleeve may include an inner sleeve portion, an outer sleeve portion, and a pressure sleeve portion. The pressure sleeve portion may be located radially inward of the outer sleeve portion and may extend forward from the inner sleeve portion. A blocker door may be hingedly coupled to the pressure sleeve portion. A drag link may be pivotably coupled to the blocker door. A forward end of the drag link may be configured to deploy radially inward in response to aft translation of the sleeve.

Abstract: A propulsion system assembly includes a variable area inlet and an inlet duct. The variable area inlet includes an outer airflow inlet passage, an inner airflow inlet passage, an inlet structure and a center body structure. The outer airflow inlet passage is between the inlet structure and the center body structure. The inner airflow inlet passage is formed within the center body structure. The center body structure includes a valve configured to regulate air flow through the inner airflow inlet passage. The valve includes a first door configured to pivot between a closed position and an open position. The inlet duct is configured to receive air from the outer airflow inlet passage when the first door is in the closed position. The inlet duct is configured to receive air from the outer airflow inlet passage and the inner airflow inlet passage when the first door is in the open position.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inner structure that extends axially along and circumferentially about an axial centerline. The nacelle inner structure includes an internal compartment and a cowl. The internal compartment is configured to house a core of a gas turbine engine. The cowl is configured to form an outer radial periphery of the internal compartment. An aft end portion of the cowl is also configured to form an outer radial periphery of a compartment exhaust to the internal compartment. The aft end portion of the cowl includes a plurality of axial fingers arranged circumferentially about the axial centerline in an array.

Abstract: A tool for fabricating a control surface is disclosed. In various embodiments, the tool includes a first block defining a longitudinal direction running between a leading edge end and a trailing edge end; a first sidewall spaced a first lateral distance from the first block to form a first closeout channel running in the longitudinal direction between the first block and the first sidewall; and a second sidewall configured to form a second closeout channel running in the longitudinal direction, the second closeout channel disposed laterally opposite the tool from the first closeout channel.

Abstract: A thrust reverser may comprise translating sleeve panel. A first articulating slider and a second articulating slider may be located at a circumferential end of the translating sleeve panel. Each of the first articulating slider and the second articulating slider may include a slider bar and a slider ball. The slider ball may be attached to the translating sleeve panel and located in a spherical opening defined by the slider bar.

Abstract: A pressure relief door assembly includes a pressure relief door, a pressure-actuated latch, and a temperature-actuated lock. The latch is disposable in each of a latched configuration (to retain the pressure relief door in a closed position) and an unlatched configuration (to allow the pressure relief door to move into an open position). The lock is disposable in each of an unlocked configuration (to allow the pressure relief door to move into the open position when the latch is in its unlatched configuration) and a locked configuration (e.g., to lock the latch in its latched configuration, to lock the pressure relief door in its closed position, or both). The lock may include a bimetallic coil, that when exposed to a temperature that satisfies a temperature threshold, expands a sufficient amount to engage a locking pin with a corresponding portion of the latch to retain the latch in its latched configuration.

Abstract: A modular tooling arrangement includes a base member comprising a planar working surface, a frame circumscribing a first cavity at least partially defined by the planar working surface, and a plurality of plates configured to be received in the first cavity for forming a second cavity of a desired shape and size. The plurality of plates at least partially define the second cavity configured to receive a work piece. The plurality of plates may be replaced with plates of various sizes to vary at least one of the size and shape of the second cavity.