Abstract: A composite panel suitable for heating an environment includes a face sheet having a 3D woven structure and abutting the environment, and a first core layer positioned on a side of the face sheet opposite the environment. The 3D woven structure includes at least one z-fiber extending in a first direction, the first direction representing a thickness of the face sheet. The woven structure further includes a plurality of weft layers, each having a weft fiber extending in a second direction, and a warp layer disposed between the plurality of weft layers, the warp layer having a warp fiber extending in a third direction. The z-fiber extends along the plurality of weft layers across a full extent of the 3d woven structure in the first direction.

Abstract: Systems and devices for angle of attack sensors are provided. Aspects include a vane, a faceplate, an annular region in the faceplate, and a thin film heater assembly attached to a surface of the annual region.

Abstract: An air data probe includes a probe body including a probe wall. The probe body is formed from a first material by direct energy metal deposition. An insert is positioned in the probe wall. The insert is formed from a second material different from the first material. The insert is encapsulated in the probe wall via the direct energy metal deposition. A method of forming an air data probe includes forming one or more thermally conductive inserts, and encapsulating the one or more inserts into a wall of an air data probe via direct energy metal deposition. The air data probe is formed from a first material and the one or more inserts are formed from a second material different from the first material.

Abstract: An air date probe includes a strut assembly extending from a base, and a tube assembly coupled to the strut assembly. One or both of the strut assembly and the tube assembly comprises a self-regulating thin film heating arrangement. The self-regulating thin film heating arrangement includes at least one circuit including a positive temperature coefficient (PTC) heating element connected in series with a negative temperature coefficient (NTC) heating element.

Abstract: In an example, a system comprises at least one body-worn tracking device (BWTD) configured to transmit location data that indicates a location of the BWTD and a computing system configured to communicate with the at least one BWTD. The computing system is configured to receive the location data from the at least one BWTD, determine, based on a set of weighted filters associated with at least one monitoring attribute, at least one gradient value corresponding to the location data, where the at least one gradient value represents a level of the at least one monitoring attribute, and perform at least one operation based on the at least one gradient value.

Abstract: An air data probe includes a probe body including a probe wall. The probe body is formed from a first material by direct energy metal deposition. An insert is positioned in the probe wall. The insert is formed from a second material different from the first material. The insert is encapsulated in the probe wall via the direct energy metal deposition.

Abstract: A method of text based knowledge mining, the method including receiving, by a processing system, a plurality of textual records from one or more data sources and extracting, by the processing system, entities from the plurality of textual records, wherein the entities represent proper nouns in the plurality of textual records. The method further includes extracting, by the processing system, characteristic phrases associated with the one or more entities from the plurality of textual records, determining, by the processing system, topic entities from the entities, wherein the topic entities define a category that one or more of the entities fall within, and performing, by the processing system, a hierarchy analysis to generate hierarchy data based on the entities, the topic entities, and the characteristic phrases.

Abstract: Provided are embodiments for a direct drive wiper system. The system includes a motor that is operably coupled to a wiper system to drive one or more wiper arms of the wiper system, and a gearbox, wherein an input to the gearbox is coupled to the motor and an output of the gearbox is coupled to the wiper assembly, wherein the gearbox is configured to convert an input from the motor to an output to drive the wiper system. The system also includes a brake and stopper mechanism that is coupled to the gearbox and the wiper system. Also provided are embodiments for a method for operating the direct drive wiper system.

Abstract: An air date probe includes a base portion, a strut portion extending from the base portion, and a tube assembly secured to an extending from the strut portion. One or more of the tube assembly or the strut portion includes a sleeve member having a sleeve outer surface positioned at a sleeve frustum angle relative to a sleeve member axis. A thin film heater is positioned at the sleeve outer surface, and the tin film heater and the sleeve member are positioned in a housing member. The housing member has a housing inner surface having a housing frustum angle such that the thin film heater is retained by compression between the housing member inner surface and the sleeve member outer surface.

Abstract: A windshield wiper system for an aircraft is provided and includes a motor, an output shaft, a wrap spring and crank rocker mechanism (WSCRM) to which the motor and the output shaft are coupled and a controller. By way of the WSCRM, first directional rotation input to the WSCRM from the motor via a two-stage gear reduction is converted such that the output shaft drives wiper blade oscillation through a first sweep angle and second directional rotation input to the WSCRM from the motor is converted such that the output shaft drives wiper blade oscillation through a second sweep angle. The controller is configured to control the motor such that the first directional rotation is continuously or non-continuously input during first or second flight conditions, respectively, and the second directional rotation is continuously input during third flight conditions.

Abstract: Disclosed is a process of manufacturing a pitot tube assembly including: obtaining a metal cylindrical tube having a first axial portion that is a first material blank for an assembly inlet portion of the pitot tube assembly and a second axial portion that is a second material blank for a body portion of the pitot tube assembly; nesting the first axial portion of the tube within a cylindrical graphite insert; nesting the cylindrical graphite insert within a cylindrical sheath; constraining axial motion of the insert; performing laser scanning to the assembly inlet portion; and performing additive manufacturing to the pitot tube assembly inlet portion.

Abstract: A pitot tube includes an outer tube extending from a first tube end to second tube end, the second tube end defining a tip portion of the pitot tube, the tip portion including an inlet opening. A tube sleeve inside of the outer tube at least partially defines a tube passage extending from the first tube end to the second tube end. The tube sleeve includes a sleeve outer surface having a sleeve body portion having a first outer diameter and a sleeve tip portion located at the tip portion of the pitot tube. The sleeve tip portion has a second outer diameter smaller than the first outer diameter. A heating element is located between the outer tube and the tube sleeve at at least the sleeve tip portion.

Abstract: Disclosed is a multilayer structure, comprising: a first heater layer comprising a CNT heater, wherein the CNT heater comprises a composite of carbon nanotubes and silicone; and a second heater layer comprising a PTC heater, wherein the PTC heater comprises a composite of carbon black and polymer; wherein the first heater layer and the second heater layer are first and second respectively in an electrical series; wherein the first heater layer has a negative temperature coefficient with respect to electrical resistivity; and wherein the second heater layer has a positive temperature coefficient with respect to electrical resistivity. Also disclosed is an aircraft component comprising the multilayer structure.

Abstract: A water tank includes a compression molded tank shell. The tank shell includes a back panel and a side panel extending from the back panel. The side panel defines an outer perimeter of the water tank. A compression molded front panel is secured to the side panel to enclose an interior of the water tank. A method of forming a potable water tank includes forming a tank shell via a compression molding process, the tank shell including a back panel and a side panel extending from the back panel, the side panel defining an outer perimeter of the water tank. A front panel is separately formed by compression molding, and the front panel is secured to the side panel thereby enclosing an interior of the water tank.

Abstract: A laser direct metal deposition method for a graphite substrate is provided. The laser direct metal deposition method includes creating an assembling by sliding an outer sheath over the graphite substrate. Further, laser direct metal deposition method includes performing a laser scanning of the outer sheath and performing a laser metal deposition over the graphite substrate with the outer sheath.

Abstract: A pitot tube includes an outer tube extending from a first tube end to second tube end. The second tube end defines a tip portion of the pitot tube. A tube sleeve is located inside of the outer tube and defines a tube passage extending from the first tube end to the second tube end. A heating element is located between the outer tube and the tube sleeve. The heating element is isolated from airflow into the tube passage. A method of forming a pitot tube includes installing a heating element to an outer surface of a tube sleeve, the tube sleeve defining a tube passage of the pitot tube. The tube sleeve is secured in an outer tube such that the heating element is between the tube sleeve and the outer tube and is isolated from airflow through the tube passage.

Abstract: A hybrid heater system for aircraft wing ice protection is provided. The hybrid heater system includes a voltage source, a carbon nano-tube (CNT) heater, a first positive temperature coefficient (PTC) heater disposed in parallel with the CNT heater to form a parallel formation and a second PTC heater disposed in series between the voltage source and the parallel formation.

Abstract: A laser direct metal deposition method for a graphite substrate is provided. The laser direct metal deposition method includes creating an assembling by sliding an outer sheath over the graphite substrate. Further, laser direct metal deposition method includes performing a laser scanning of the outer sheath and performing a laser metal deposition over the graphite substrate with the outer sheath.

Abstract: An imaging probe (102) for use in measuring surface roughness by angular speckle correlation is shown. The imaging probe comprises a first illumination fibre (201) to illuminate a sample location (103) on a surface, and having an input end for coupling of coherent light into the fibre, and an output end cleaved at an angle ?1, a second illumination fibre (202) to illuminate the sample location on the surface, and having an input end for coupling of coherent light into the fibre, and an output end cleaved at an angle ?2 that is different from ?1, and an image transmission system (204) for transmission of a speckle pattern caused by illumination of the sample location on the surface by coherent light from either the first illumination fibre or the second illumination fibre.

Abstract: A method and an information handling system (IHS) renders a graphical user interface (GUI) from a remote device using a local storage. An interface controller detects a first event used to initiate access to the GUI at the remote device. The controller requests GUI frame buffer data corresponding to the first event, and GUI change data from the remote device. The GUI change data correspond to respective events that can trigger changes to the GUI. In response to receiving the requested data, the controller provides a first locally-rendered GUI using the GUI frame buffer data. The controller stores the GUI change data in local storage. The controller then detects a second event/interaction via the first locally-rendered GUI and retrieves from local storage a relevant portion of the GUI change data. The controller provides an updated locally-rendered GUI using the relevant portion of GUI change data.