Abstract: A conductive ink may comprise a high temperature thermoplastic polyurethane (TPU) and a plurality of conductive particles disposed in the high temperature TPU. The plurality of conductive particles may comprise between 60% and 95% of the conductive ink by weight. The high temperature TPU may include a melting point between 120° C. and 200° C. The conductive ink may be used for external heated composite structures, such as rotor blades, fixed wings, faring, engine lip electrothermal ice protection, or the like. The conductive ink may have enhanced mechanical fatigue resistance.

Abstract: A light emitting diode display panel may comprise a substrate, a plurality of light emitting diodes located over the substrate, and an optical assembly located over the plurality of light emitting diodes. The optical assembly may include a lens array and a diffuser. An inner surface of the lens array may define a plurality of inner curves.

Abstract: A method of touchless activation of an electrically activated device may comprise: receiving, via a processor and through a sensor in an aircraft cabin, gesture data; comparing, via the processor, the gesture data to a predetermined gesture, the predetermined gesture being created by transitioning a hand from a first position to a second position, one of the first position and the second position being a closed fist, a remainder of the first position and the second position being an open palm; determining, via the processor, whether the gesture data matches the predetermined gesture; and commanding, via the processor, the electrically activated device to change from a first state to a second state.

Abstract: Provided are embodiments for performing automated defect detection for a flexible member using image processing. The techniques include monitoring, by one or more sensors, a flexible member to obtain sensor data, converting the sensor data from the one or more sensors to image data, and receiving reference image data to compare to the image data. The techniques also include determining a defect based on the comparison and threshold setting information for the flexible member, and transmitting a notification based on the defect.

Abstract: A portable container for being loaded into and unloaded from a compartment of an aircraft, the portable container comprises a power source comprising one or more rechargeable batteries and coupling circuitry configured to electrically couple one or more of the rechargeable batteries to an electrical connector, and a housing comprising the power source, wherein the power source is operable to discharge one or more of the rechargeable batteries and transmit a discharge current via the electrical connector, and wherein the electrical connector comprises an interface portion operable to be physically connectable with a corresponding interface portion of another electrical connector to electrically couple the electrical connector to the another electrical connector.

Abstract: A method of fabricating a composite component, includes forming a fibrous preform by forming a first ceramic particle layer over a first textile layer, the first ceramic particle layer having a first group of ceramic particles, disposing a second textile layer over the first ceramic particle layer, forming a second ceramic particle layer over the second textile layer, the second ceramic particle layer having a second group of ceramic particles, and disposing a third textile layer over the second ceramic particle layer. The method further includes densifying the fibrous preform.

Abstract: A power drive unit (PDU) having a magnetic hold brake for use in an aircraft is disclosed herein. The PDU includes a wheel configured to convey cargo through a portion of the aircraft, a motor coupled to the wheel, a brake disk, a solenoid configured to apply a first force to move the brake disk in a first direction to resist rotation of the motor, wherein the solenoid is further configured to apply a second force to move the brake disk in a second direction opposite the first direction to allow the motor to rotate, and a magnet configured to apply a third force to the brake disk, the third force being in the first direction to apply a drag force to the motor.

Abstract: A heat shield panel comprising an inner heat shield layer and an outer heat shield layer, the inner heat shield layer and the outer heat shield layer each having two outer edges wherein the outer edges of the inner heat shield layer and the outer edges of the inner heat shield layer are substantially aligned and are affixed to each other to form heat shield panel edges, and wherein the inner heat shield layer is formed of two or more segments each having an inner edge, the inner edges of the segments being arranged to move relative to each other.

Abstract: A torque plate barrel for use with a brake system is disclosed herein. The torque plate barrel includes a barrel body having an outer diameter, an inner diameter, and an axial length extending from a first end to an opposing second end, wherein the inner diameter varies along the axial length and the outer diameter is fixed along the axial length.

Abstract: An internal heating trace assembly may include a first bus bar, a second bus bar, a plurality of ceramic positive temperature coefficient (PTC) elements, and an insulator. The ceramic PTC elements may be disposed in parallel between the first bus bar and the second bus bar. The insulator may include a heat-shrink tubing. The ceramic PTC element may include a PTC strip or a PTC bead.

Abstract: A system for repositioning rails in a cargo bay of an aircraft. The system includes a base configured to be coupled to a structure in the cargo bay and having a first side and a second side. The system further includes a cradle for receiving a rail for restricting movement of a unit load device (ULD) in at least one direction, the cradle configured to position the rail between a first position and a second position in which the rail is closer to the second side of the base than when the rail is in the second position.

Abstract: A metallic part is disclosed. The part may comprise a functionally graded monolithic structure characterized by a variation between a first material composition of a first structural element and a second material composition of at least one of a second structural element. The first material composition may comprise an alpha-beta titanium alloy. The second material composition may comprise a beta titanium alloy.

Abstract: A hybrid water storage system for an aircraft includes separate variable volumes for respectively storing/holding potable water and gray water occupying a common container. The hybrid water storage system is generally configured to draw potable water from a first variable volume in order to provide fresh water to one or more aircraft appliances (e.g., sinks, showers, ice-makers, etc.), and the used potable water (i.e., the potable water that is collected in drains from the aircraft appliances), referred to herein as gray water, is routed to a second variable volume that occupies the same container as the first variable volume.

Abstract: A piston assembly for engaging two selectively engageable parts comprising: a housing defining a piston cylinder; a piston; and an adjuster assembly comprising: a piston stroke limiter configured to limit the length of a return stroke of the piston from an extended stroke position and a retracted stroke position, the piston stroke limiter comprising a spring and a spring guide; and a crushable body, acting between the piston and the piston stroke limiter, the crushable body being arranged to reduce in axial length when a length of an extension stroke exceeds a length of a retraction stroke to maintain the length of the return stroke; wherein the crushable body comprises an inner crushable thin-walled tube surrounding at least a portion of the piston and an outer crushable thin-walled tube mounted around and radially outwards of the inner crushable tube.

Abstract: A temperature compensating shock strut health indicator system for use with a shock strut comprises a visual indicator comprising a plurality of sectors and a pointer configured to rotate with respect to the visual indicator to point to one of the plurality of sectors. The sector to which the pointer points to is dependent on the shock strut stroke (i.e., the position of the piston with respect to the cylinder). In various embodiments, the visual indicator includes various rings that correspond to a different temperature compensated ideal stroke whereby a crew member can correspond the pointer to the appropriate ring depending on ambient temperature. In various embodiments, the pointer comprises a temperature sensitive material configured to cause the pointer to rotate with respect to the visual indicator to actively compensate for temperature.

Abstract: A veneer panel may include a face veneer, a first inner layer bonded to the face veneer, a second inner layer bonded to the first inner layer, and a thermally conductive layer bonded to the second inner layer. The first inner layer and the second inner layer are treated with a flame retardant. The first inner layer is disposed between the face veneer and the second inner layer, and the second inner layer is disposed between the first inner layer and the thermally conductive layer.

Abstract: A solid propellant propulsion motor may comprise: a forward propellant grain extending along a longitudinal axis of a motor case between a forward end of the motor case and a first burn inhibitor layer in the motor case; the first burn inhibitor layer disposed axially adjacent to the forward propellant grain; an aft propellant grain disposed axially adjacent to the first burn inhibitor layer; a second burn inhibitor layer disposed axially adjacent to an aft end of the aft propellant grain; and an ablative material layer disposed on a radially inner surface of the aft propellant grain.

Abstract: Systems and methods for casting solid propellants include a mandrel for forming geometric features in a perforation of a propellant grain. In various embodiments, the mandrel includes a frangible portion that is removed from the propellant grain after the propellant grain has cured around the mandrel. A second portion of the mandrel may be left behind in the propellant grain. The mandrel may include a support structured disposed in the through hole of the mandrel. The support structure may include a plurality of longitudinal channels for directed exhaust gasses through the mandrel upon ignition of the propellant grain.

Abstract: A pneumatic valve for attachment to a source of high pressure gas comprises a valve body which comprises a gas inlet and a gas outlet. A rupturable membrane extends across the gas inlet. A membrane support element is slidably supported in the valve body for movement between an extended position and a retracted position, the membrane support element having a lower end engageable, in the extended position, with the rupturable membrane to support the rupturable membrane against rupture. The valve body further comprises a bore through which the membrane support element extends and one or more gas supply passages bypassing the bore for providing a gas flow path from the gas inlet to the gas outlet. The membrane support element is configured to be movable from the extended position to the retracted position to permit the rupturable membrane to rupture under the pressure of the high pressure gas.

Abstract: A landing gear actuation system is disclosed herein. The landing gear actuation system includes a trunnion sprocket coupled to a movable member, a drive motor, and a flexible drive member extending between and to the motor and the trunnion sprocket. The motor is configured to move the flexible drive member, wherein the movement of the flexible drive member moves the trunnion sprocket and the movable member. The flexible drive member may be a belt or a chain.