Abstract: A heater panel includes a core and a heater/dielectric layer including a positive thermal coefficient (PTC) heater layer between a pair of dielectric layers. A structural facing is included, wherein the heater/dielectric layer is bonded directly between the core and the structural facing. A second structural facing can be bonded to the core opposite the heater/dielectric layer. An impact layer can be bonded to the structural facing, e.g., the first structural facing described above, opposite the heater/dielectric layer.

Abstract: A heater panel includes a core. A heater/dielectric layer including a positive thermal coefficient (PTC) heater layer between a pair of dielectric layers is bonded to the core in a stack. An impact layer is bonded to the stack, wherein the impact layer includes a first sub-layer for impact absorption that is bonded to the stack and a second sub-layer for cut resistance bonded to the first sub-layer. The second sub-layer has a higher material hardness than that of the first-sub layer.

Abstract: A heated floor panel assembly with an impact layer is made to absorb blunt force and protect a heating element inside the assembly. The assembly further includes a plurality of structural layer made of a reinforced polymer matrix, one or more core layer with a honeycomb or foam structure for absorbing shear stress, and a heating layer containing the heating element. The impact layer is a composite layer with a resin impregnated fiber matrix.

Abstract: A heater panel includes a core and a heater/dielectric layer including a positive thermal coefficient (PTC) heater layer between a pair of dielectric layers. A structural facing is included, wherein the heater/dielectric layer is bonded directly between the core and the structural facing. A second structural facing can be bonded to the core opposite the heater/dielectric layer. An impact layer can be bonded to the structural facing, e.g., the first structural facing described above, opposite the heater/dielectric layer. The heater layer can be formed by direct writing a heating element pattern onto a dielectric layer bonded to the core.

Abstract: A heated floor panel assembly for aircraft includes an impact layer made from a 2-D or 3-D woven high temperature thermoplastic fiber matrix impregnated with a resin. The impact layer can further include woven metallic fibers. The assembly also includes a stack of structural layers, a heating layer, and a core layer for absorbing shear stress.

Abstract: A heated floor panel assembly contains a positive temperature coefficient heater secured in the assembly through a number of welded joints through a thermoplastic dielectric layer. The positive temperature coefficient heater is on a thermoplastic substrate, which is bonded to the thermoplastic dielectric layer. The assembly further includes an impact layer, a core layer, and structural layers.

Abstract: A heated floor panel assembly for aircraft includes structural layers made of a fiber matrix and a high temperature thermoplastic resin. The structural layers are within the heated floor panel assembly to protect the other assembly components from damage and absorb stress. The heated floor panel assembly further includes a heating layer with a heating element, an impact layer, and a core layer to take shear stress exerted on the assembly.

Abstract: A crystalline precursor compound for manufacturing a lithium transition metal based oxide powder usable as an active positive electrode material in lithium-ion batteries, the precursor having a general formula M(O)x(OH)2-x-y(CO3)y, with 0<x?1, 0<y<0.03 and M=NiaMnbCocAd. A being a dopant, with 0.30?a<0.90, 0.10?b<0.40, 0.10?c<0.40, d<0.05 and a+b+c+d=1, the precursor having a Na content less than 200 ppm, a S content less than 250 ppm, the precursor having a specific surface area with a BET value expressed in m2/g and a tap density TD expressed in g/cm3, with a ratio BET/TD>30.104 cm5/g2.

Abstract: The lamp includes a substantially transparent housing tube, a first end cap at a first end of the housing tube and a second end cap at a second end of the housing tube. The end caps include contacts for electrically contacting a power supply. An LED-filament is arranged in the housing tube between the first end cap and the second end cap.

Abstract: A multirotor aerial vehicle (MAV) is disclosed. The MAV includes a housing, a plurality of rotatable arms, wherein each of the plurality of rotatable arms has a proximal end coupled to the housing and a distal end configured to rotate about a vertical axis passing through the proximal end of the corresponding arm, a plurality of thrust-generating rotors, each coupled to a corresponding one of the plurality of rotatable arms at the corresponding distal end, a flight controller configured to selectively control each of the plurality of thrust-generating rotors, and a flight trim controller configured to control rotation of the plurality of rotatable arms in order to adjust the geometric center of the rotors of the MAV from a first center of gravity (CoG) associated with the MAV in an unloaded state to a second CoG associated with the MAV in a loaded state.

Abstract: A method for reducing the resistivity of a thermoplastic film containing carbon nanotubes includes connecting an electric power supply to the thermoplastic film containing carbon nanotubes and passing electric current through the thermoplastic film containing carbon nanotubes to heat the thermoplastic film to an elevated temperature and align carbon nanotubes within the thermoplastic film. The thermoplastic film is solid at room temperature.

Abstract: Composite powder for use in an anode of a lithium ion battery, whereby the particles of the composite powder comprise silicon-based domains in a matrix, whereby the individual silicon-based domains are either free silicon-based domains that are not or not completely embedded in the matrix or are fully embedded silicon-based domains that are completely surrounded by the matrix, whereby the percentage of free silicon-based domains is lower than or equal to 4 weight % of the total amount of Si in metallic or oxidized state in the composite powder.

Abstract: Disclosed is an attachment between a bus bar and a nano-carbon heater used for de-icing and/or anti-icing in an aircraft or other vehicle. The attachment between the bus bar and the heater is created through a coupling agent, a pre-preg glass fabric, and a conductive adhesive. This attachment allows for electrical connections to be made to the heater via the bus bar, and the attachment is strong enough to withstand stress from thermal cycles.

Abstract: A system of near-bit measurement while drilling system includes motor system, measurement transmission system, wireless receiving system and non-magnetic short sub. The measurement transmission system is set inside the motor system, and the transmitting device from the measurement transmission system and the receiving device from the wireless receiving system are set inside the non-magnetic cavity. In the process of drilling via drill bit, the azimuth gamma and the well deviation parameters on the formation where the drill bit is located is able to be measured in real time more accurately and then will make real-time wireless transmission toward the wireless receiving system. Compared with conventional measurement while drilling work, the measurement location of the near-bit measurement while drilling system is nearer to the drill bit with non-hysteretic description of well trajectory and formation gamma measurement so as to enhance the drilling-encounter ratio significantly.

Abstract: A carbon allotrope heating element includes an electrical resistivity between 0.005 ohms per square (?/sq) and 3.0 ?/sq. A heating system includes a component and a carbon allotrope heating element having an electrical resistivity between 0.005 ?/sq and 3.0 ?/sq. A method includes modifying a carbon allotrope heating element to have an electrical resistivity between 0.005 ?/sq and 3.0 ?/sq and applying the carbon allotrope heating element to a component of an aircraft.

Abstract: A heating circuit assembly and method of manufacture includes an electrically conductive heating element having a pattern. An electrically non-conductive substrate is additive manufactured and secured to the element for structural support. The substrate has a topology that generally aligns with the pattern of the element thereby reducing the assembly weight and minimizing substrate material waste.

Abstract: An ice protection assembly includes a pneumatic de-icer attached to an aircraft surface by a vertically aligned carbon nanotube loaded adhesive. The adhesive can be a pressure sensitive adhesive or a chemical adhesive loaded with vertically aligned carbon nanotubes.

Abstract: A strut for a gas turbine engine includes an airfoil section extending in a spanwise direction between a first platform and a second platform, extending in a chordwise direction between a leading edge and trailing edge to define a chord length, and extending in a thickness direction between a first side and a second side to define a chord width. Exterior surfaces of the airfoil section define a leading portion between the leading edge and a widest location of the airfoil section relative to the thickness direction, and a trailing portion between the widest location and the trailing edge. The exterior surfaces establish a respective exterior contour for each span position between a 0% span position and a 100% span position. The exterior surfaces define a plurality of dimples in the leading portion.

Abstract: A heating element includes a bottom layer, a web consisting of a carbon nanotube (CNT) yarn wherein the web is affixed to a first side of the bottom layer, and an encapsulating layer positioned on the web and the first side of the bottom layer. A method for making a heating element includes providing a bottom layer, inserting a plurality of pegs into the bottom layer such that a portion of each peg protrudes from the bottom layer, weaving a CNT yarn around the protruding portions of the plurality of pegs to form a CNT web, affixing the CNT web to the bottom layer, and encapsulating the CNT web and the bottom layer to form the heating element.

Abstract: A floor panel assembly includes an insulating layer which protects a sheet heater, first and second structural layers, and a honeycomb layer for support. The floor panel assembly allows for heating of the cabin of an aircraft without mechanical damage to the sheet heater.