Abstract: A method may comprise: laying up a first plurality of plies of material comprising thermoplastic resin and fiber to form an inner skin preform, the inner skin preform being a continuous sheet including alternating peaks and valleys; laying up a second plurality of plies of material comprising thermoplastic resin and fiber to form an outer skin preform; and joining the inner skin preform to the outer skin preform.

Abstract: An information handling system includes a bottom case and a wireless charging puck. The bottom case includes a bay. The wireless charging puck fits into the bay, and is detachable from the bottom case. When the wireless charging puck is fitted into the bay, the wireless charging puck is configured as a power receiving unit to receive wireless power. When the wireless charging puck is detached from the bay, the wireless charging puck is configured as a power transmitting unit to provide wireless power to an external device.

Abstract: The disclosure relates to compositions comprising a first structure of the formula: or a salt thereof, wherein R1, R2, R3, Ar1, and n are defined herein. Materials, devices, and methods of using such compositions are also described.

Abstract: Apparatuses, methods, and systems for a hinge feed antenna of eyewear, are disclosed. One apparatus includes a front frame, a temple arm, and a hinge rotatably connecting the front frame and the temple arm. For an embodiment, the temple arm includes a circuit assembly including at least a radio. For an embodiment, the front frame includes one or more antennas traces, wherein the hinge conductively connects the circuit assembly to the one or more antenna traces. The apparatus further includes an antenna tuner located between the circuit assembly and the hinge, wherein a rotation position of the temple arm is sensed, wherein the rotation position is dependent on an orientation of the front frame relative to the temple arm; and wherein the antenna tuner includes an impedance tuner for adaptively adjusting an input impedance of the impedance tuner based on the sensed rotation position of temple arm.

Abstract: An acoustic panel system is provided that includes a perforated first skin, a second skin and a core. The core is connected to the perforated first skin and the second skin. The core includes a plurality of chambers and a first constriction. Each of the chambers extends vertically through the core between the perforated first skin and the second skin. The chambers include a first chamber. The first constriction is configured to divide the first chamber into a plurality of fluidly coupled sub-chambers. The first constriction is configured from or otherwise includes a shape memory material.

Abstract: A method is provided during which a preform is provided that includes an electric heater and thermoplastic material. The preform is consolidated to provide an aircraft component. The consolidating includes heating the thermoplastic material using the electric heater. The electric heater is embedded within the thermoplastic material of the aircraft component. The electric heater is configured as a part of a thermal anti-icing system for melting and/or preventing ice accumulation on an exterior surface of the aircraft component.

Abstract: A method is provided during which a composite preform is provided that includes an electric heater, fiber-reinforcement and thermoset material. The composite preform is consolidated to provide a composite aircraft component. The consolidating includes heating the thermoset material using the electric heater to cure the thermoset material. The electric heater and the fiber-reinforcement are embedded within the cured thermoset material. The electric heater is configured as a part of a thermal anti-icing system for melting and/or preventing ice accumulation on an exterior surface of the composite aircraft component.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes an aircraft control surface. The aircraft control surface includes a first skin, a second skin and a support structure laterally between and connected to the first skin and the second skin. The support structure includes a spar, a first stiffener and a second stiffener. The spar extends spanwise within the aircraft control surface. The first stiffener extends longitudinally within the aircraft control surface to the spar. The second stiffener extends longitudinally within the aircraft control surface to the spar. An actuator receptacle projects longitudinally into the aircraft control surface from a base of the aircraft control surface to the spar. The actuator receptacle extends spanwise within the aircraft control surface between the first stiffener and the second stiffener.

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: A wing panel actuator assembly includes: an actuator housing; an actuator piston arranged in the actuator housing and axially movable relative to the actuator housing; a connecting rod attached, at one end, to an end of the piston extending from the actuator housing; the actuator housing and piston arranged to be accommodated inside a movable panel of an aircraft wing. The connecting rod is arranged to be attached, in use, at its end opposite the one end attached to the piston, to a wing structure of the aircraft wing, the panel being pivotable about a pivot point P relative to the wing structure by means of the actuator piston.

Abstract: An assembly is provided for an aircraft. This aircraft assembly includes an aircraft control surface. The aircraft control surface includes a first skin, a second skin and a support structure laterally between and connected to the first skin and the second skin. The support structure includes a spar, a first stiffener and a second stiffener. The spar extends spanwise within the aircraft control surface. The first stiffener extends longitudinally within the aircraft control surface to the spar. The second stiffener extends longitudinally within the aircraft control surface to the spar. An actuator receptacle projects longitudinally into the aircraft control surface from a base of the aircraft control surface to the spar. The actuator receptacle extends spanwise within the aircraft control surface between the first stiffener and the second stiffener.

Abstract: An airfoil body is provided for an aircraft which includes a first skin, a second skin, a plurality of first stiffeners and a plurality of second stiffeners. The first stiffeners are configured from or otherwise include first stiffener composite material. The first stiffeners extends widthwise between and are connected to the first skin and the second skin. Each of the first stiffeners has a first stiffener longitudinal centerline that extends spanwise along the first skin and the second skin. The second stiffeners are configured from or otherwise include second stiffener composite material. The second stiffeners extend widthwise between and are connected to the first skin and the second skin. Each of the second stiffeners has a second stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin.

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 assembly is provided for an aircraft. This aircraft assembly includes an aircraft control surface and a hydraulic actuator. The hydraulic actuator includes a housing and a piston within the housing. The housing is formed integral with the aircraft control surface.

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 door includes a backskin including an interior surface and an exterior loft surface. The thrust reverser door further includes a cover plate including a cover plate body having a first side and a second side opposite the first side. The thrust reverser door further includes a grid structure mounted to the second side of the cover plate body and the interior surface of the backskin.

Abstract: A manufacturing process is provided during which a thrust reverser cascade is formed for an aircraft propulsion system. During the formation of the thrust reverser cascade, a first panel of material is stamped into a first corrugated body. A second panel of material is stamped into a second corrugated body. The first corrugated body is bonded to the second corrugated body.

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 control surface for an aircraft may comprise an outer skin and a core coupled to the outer skin. The core may include a plurality of corrugations. A height of the core may decrease in a direction extending from a leading edge of the control surface to a trailing edge of the control surface.

Abstract: An airfoil body is provided for an aircraft which includes a first skin, a second skin, a plurality of first stiffeners and a plurality of second stiffeners. The first stiffeners are configured from or otherwise include first stiffener composite material. The first stiffeners extends widthwise between and are connected to the first skin and the second skin. Each of the first stiffeners has a first stiffener longitudinal centerline that extends spanwise along the first skin and the second skin. The second stiffeners are configured from or otherwise include second stiffener composite material. The second stiffeners extend widthwise between and are connected to the first skin and the second skin. Each of the second stiffeners has a second stiffener longitudinal centerline that extends lengthwise along the first skin and the second skin.