Abstract: A method is disclosed, which can comprise via a transonic gas jet, depositing a thin film of LiPON on a substrate via a directed vapor deposition process. The transonic gas jet transports a thermally evaporated vapor cloud comprising the LiPON, wherein, the transonic gas jet comprises one of (a) substantially entirely nitrogen (N2) gas; or (b) nitrogen (N2) gas as a dopant in a concentration greater than 10% by volume in an inert carrier gas.

Abstract: Certain exemplary embodiments can provide a method, which can comprise via a transonic gas jet, depositing a thin film of LiPON on a substrate via a directed vapor deposition process. The transonic gas jet transports a thermally evaporated vapor cloud comprising the LiPON, wherein, the transonic gas jet comprises one of (a) substantially entirely nitrogen (N2) gas; or (b) nitrogen (N2) gas as a dopant in a concentration greater than 10% by volume in an inert carrier gas.

Abstract: An intravaginal device having an aperture and a withdrawal assembly. The withdrawal assembly has a withdrawal member and an obstruction.

Abstract: An intravaginal device having an aperture and a withdrawal assembly. The withdrawal assembly has a withdrawal member and an obstruction.

Abstract: An intravaginal device having an aperture and a withdrawal assembly. The withdrawal assembly has a withdrawal member and an obstruction.

Abstract: An intravaginal device having an aperture and a withdrawal assembly. The withdrawal assembly has a withdrawal member and an obstruction.

Abstract: An intravaginal device having an aperture and a withdrawal assembly. The withdrawal assembly has a withdrawal member and an obstruction.

Abstract: An engine nacelle inlet lip includes both acoustic treatment and electric heating for ice protection. The inlet lip has a composite outer skin and a composite inner skin, with the composite outer skin having at least one integrated heater element embedded in the composite material. An acoustic cellular core positioned between the outer and inner skin acts to attenuate fan noise from the engine. Covering the outer skin and overlying the acoustic core is a perforated erosion shield having a first set of openings that pass entirely thorough its thickness. The composite outer skin includes a second set of openings such that sound waves can pass from an inner barrel portion of the inlet lip through the erosion shield, outer skin, and heater element to the underlying acoustic cellular core.

Abstract: The invention includes a composite ice protection heater for an aircraft. The composite heater includes at least one electrically insulating layer, and at least one electric heater element comprising an electrically conductive layer bonded to the insulating layer. The conductive layer may include a pre-impregnated woven fabric that includes a plurality of threads that include an electrically conductive material, such as carbon or graphite fibers. The composite heater can be incorporated into a composite surface structure of an aircraft. The conductive layer and insulating layer may include a plurality of spaced openings through the layers that cooperate with an underlying open-cell matrix to attenuate noise at the associated surface of an aircraft. A desired electrical resistance of the conductive layer may be obtained by introducing a plurality of discontinuities in the layer, such as spaced holes or slits.

Abstract: An electro-thermal ice protection system for an airfoil comprises: a metal foil heater including an integral parting strip, the metal foil heater configurable to cover at least a portion of a leading edge of the airfoil with the integral parting strip disposed along an air-stagnation zone of the leading edge; and a controller coupled electrically to the metal foil heater for controlling electrical energy from a power source to the metal foil of the heater in accordance with a pulse duty-cycle and for controlling power to the parting strip of the heater to maintain the air-stagnation zone virtually free of ice formation.

Abstract: An aircraft wing (12) comprising a structural casing (14) defining a leading edge, a fuel cell (16) within the structural casing (14), a deicer (18) having electrical lines which receive a supply of electrical power from an onboard power source, and a trip line (20). The trip line (20) is positioned to receive early contact upon impact of the wing by a bird or other foreign object and disruption of the trip line triggers termination of the supply of electrical power to the deicer (18).

Abstract: Spiral wound tubes may be formed utilizing the method and apparatuses described herein. The method includes providing a mandrel and a web material having a first overlap region and a second overlap region. A binding agent is applied to at least one of the overlap regions. The mandrel is wrapped with the web material such that the second overlap region covers the first overlap region of the previously wound web and the binding agent is disposed between the previously wound first overlap region and the currently wound second overlap region. The spiral wound tubes of the invention demonstrate improved axial crush resistance.