Abstract: This invention generally relates to substituted imidazopyridine compounds, particularly substituted 4-(imidazo[1,2-a]pyridin-2-yl)benzamide compounds and salts thereof. This invention also relates to pharmaceutical compositions and kits comprising such a compound, uses of such a compound (including, for example, treatment methods and medicament preparations), processes for making such a compound, and intermediates used in such processes.

Abstract: A carbon allotrope element includes a carbon allotrope layer formed from a carbon allotrope material impregnated with a dielectric resin and having a first surface. The carbon allotrope element further includes a first bus bar in communication with the first surface, and a second bus bar in communication with the first surface and non-adjacent to the first bus bar. The first surface includes a layer of the dielectric resin and a plurality of abraded regions, and each of the first and second bus bars is in communication with one of the plurality of abraded regions of the first surface.

Abstract: Bifidobacterium animalis and application of a compound bacterium preparation prepared from the Bifidobacterium animalis in the preparation of a medicine for treating or preventing avian influenza virus infection. The invention discovers that Bifidobacterium animalis ATCC Accession No. 25527 can be used for treating animals infected by H7N9, and after the Bifidobacterium animalis ATCC Accession No. 25527 is compounded with Bifidobacterium pseudolongum ATCC Accession No. 25526, the effect is better. The compound preparation can regulate the body immune response, remarkably improve the weight loss and lung tissue injury caused by H7N9 influenza virus infection, and obviously improve the survival rate of mice infected by H7N9 influenza virus. The compound probiotic preparation provided by the invention has a remarkable effect of resisting H7N9 influenza virus infection, and can be effectively used for preventing and treating avian influenza virus infection.

Abstract: Additively manufactured heating elements for tubes are made from a positive temperature coefficient heater ink printed on the tube. A bus bar is likewise printed onto the tube using a conductive ink. The positive temperature coefficient heater ink and bust bar conductive ink are encapsulated with a closing adhesive.

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: 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: An ice protection system may include a rotary blade, an electrothermal heater, and a low ice adhesion surface. The low ice adhesion surface may include an adhesion strength below 100 kPa. The rotary blade may be disposed between the electrothermal heater and the low ice adhesion surface. The electrothermal heater may be disposed between the low ice adhesion surface and the rotary blade. The low ice adhesion surface may include a coating or a surface treatment.

Abstract: A method for forming an aircraft component includes forming an inner portion of the aircraft component. The method further includes forming an outer layer of the aircraft component using extrusion of an elastomeric material. The method further includes coupling the outer layer of the aircraft component to the inner portion of the aircraft component.

Abstract: A method for forming a deicer includes forming a body of the deicer. The method further includes forming an outer layer of the deicer through extrusion of an elastomeric material. The method further includes coupling the outer layer of the deicer to the body of the deicer.

Abstract: An airfoil includes pressure and suction sides that extend between a leading edge and a trailing edge. The airfoil has a camber line along an airfoil section that is equidistant between the exterior surface of the pressure and suction sides. The camber line extends from a 0% camber position at the leading edge to a 100% camber position at the trailing edge. A ratio of a maximum thickness to an axial chord length is between 0.2 and 0.5. The maximum thickness is located along the camber line between about 13% and 38% camber position.

Abstract: Disclosed is the use of a boron nitride nanotube (BNNT) fabric as a skin for protection of nano-carbon heaters used for de-icing aircrafts or other vehicles. This allows the heaters to be resistant to hail, bird, and other mechanical striking damages, and can be applied to parts of aircraft that require acoustic protection.

Abstract: A heating element is provided with a conductive path pattern which can be printed in a mask-free manner (e.g., drop-on-demand) with existing printing technology. The printing step can be performed, for example, with a thermal inkjet printer, a piezoelectric inkjet printer, an aerosol jet printer, or an ultrasound printer. The ink solution can be formulated so that it establishes an electrically conductive path which is free of polymer binders.

Abstract: A method of manufacturing a cured vessel is disclosed herein. The method comprises wrapping a first bladder in a first composite laminate, wrapping a second bladder in a second composite laminate. The method further comprises joining the first composite laminate and the second composite laminate by wrapping them both in a third composite laminate to form an un-cured vessel. The un-cured vessel is cured by heating the uncured vessel and pressurizing the bladder while the uncured vessel is in a vessel mold.

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 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 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: An ice protection assembly on an airfoil includes a heater positioned on the leading edge, and one or more ice phobic layers positioned to inhibit runback ice formation on the surface of the airfoil downstream of the heater.

Abstract: This invention generally relates to substituted imidazopyridine compounds, particularly substituted 4-(imidazo[1,2-a]pyridin-2-yl)benzamide compounds and salts thereof. This invention also relates to pharmaceutical compositions and kits comprising such a compound, uses of such a compound (including, for example, treatment methods and medicament preparations), processes for making such a compound, and intermediates used in such processes.

Abstract: A method of making a carbon nanotube heater includes impregnating a dry carbon nanotube fiber matrix with a conductive resin, the conductive resin is made of an organic resin and a conductive filler material. The carbon nanotube heater is lightweight, strong, and maintains appropriate electrical conductivity and resistance for use as a heater.

Abstract: An aircraft may include a fuselage and a wing extending away from the fuselage to a wing tip. The wing may have a leading edge portion, a suction side portion, and a pressure side portion. A thermoelectric element may be coupled to an inner surface of the wing. A chemical adhesive may be disposed on a thermoelectric inner surface. A structural rib may be adhesively bonded to the thermoelectric element by curing the chemical adhesive. The structural rib may be mechanically fastened to a suction side of the wing and to a pressure side of the wing.