Abstract: An apparatus may comprise: a metal pipe portion extending from a first end to a first transition end and defining a first radially outer surface and a first radially inner surface, the first transition end comprising a first tooth element and a second tooth element disposed circumferentially adjacent to the first tooth element; and a polymeric pipe portion having a second transition end and defining a second radially outer surface and a second radially inner surface, the second transition end having a complimentary shape to the first transition end, the second transition end coupled to the first transition end.

Abstract: A method of determining whether a landing event of an aircraft is hard may comprise: receiving, by a controller via a stroke position sensor, a stroke profile as a function of time for a shock strut; receiving, by the controller via a gas pressure sensor, a gas pressure in a gas chamber of the shock strut; receiving, by the controller via a wheel speed sensor, a wheel speed of a tire in a landing gear assembly; calculating, by the controller, multiple time dependent functions based on the stroke profile of the shock strut, based on the gas pressure, a shock strut temperature, and the wheel speed; and comparing, by the controller, the multiple time dependent functions to respective predetermined thresholds to determine whether the landing event is hard.

Abstract: An apparatus configured to measure the output of a rotary actuator unit includes a rotary actuator unit. The unit includes a stationary portion, a rotating portion, and a main rotational axis (L) that runs in an axial direction from a first end of the rotary actuator unit to a second end of the rotary actuator unit. The first end is opposite the second end. The apparatus also includes a linear position sensor comprising a follower, a sensor, and a sensor arm, wherein the follower is attached to the sensor by sensor arm; and wherein the sensor is attached to the stationary portion. The apparatus also includes a follower track attached or formed in, or on, to the rotating portion. The follower track is aligned in the circumferential direction that is perpendicular to axial direction of the main rotational axis (L). The follower is configured to follow the follower track.

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 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: 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 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 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 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 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 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 method of determining operating conditions of an exterior aircraft light comprising at least one light source includes: operating the at least one light source of the exterior aircraft light; repeatedly detecting light with a light detector, which is located at the exterior aircraft light and configured for providing light detection values; determining a smallest light detection value (Imin) provided by the light detector within a first period of time, and storing said smallest light detection value (Imin) as an element of a series of smallest light detection values (Imin); and evaluating the light detection values and the series of smallest light detection values (Imin) for detecting erosion of an optical component of the exterior aircraft light, for detecting the presence of ambient light and/or for detecting the presence of fog and/or clouds in front of the exterior aircraft light.

Abstract: An aircraft navigation light, configured to be usable as any of a left forward navigation light, a right forward navigation light, and a tail navigation light of an aircraft, comprises a common support plate which is substantially vertical in the aircraft frame of reference; a first light source arranged on the common support plate for emitting red light; a second light source arranged on the common support plate for emitting green light; a third light source arranged on the common support plate for emitting white light; a driving circuit coupled to the first light source, the second light source and the third light source and configured to supply power to a selected one of the first light source, the second light source, and the third light source; and a blocking element arranged to limit the light output of the aircraft navigation light to one lateral side.