Abstract: Disclosed herein is an inflow cannula for an implantable blood pump assembly. The inflow cannula includes a tubular body that extends from a proximal end to a distal end. The tubular body includes a proximal portion adapted for connection to a pump housing, and a distal portion adapted for positioning within an opening formed in a heart. The inflow cannula further includes an expandable sleeve coupled to an exterior surface of the distal portion. The sleeve has a first portion coupled to the distal portion of the tubular body, and a second portion extending from the distal end of the tubular body. The second portion is deployable from a first, stored configuration to a second, deployed configuration in which the second portion expands radially to engage and conform to an endocardial surface of the heart.

Abstract: Methods of manufacturing metal, metal-matrix, metal-metal-matrix composite weapon barrels offer barrels with improved thermal performance and rigidity with no, minimal or negative weight increase. A barrel may include a barrel core surrounded by a lightweight, thermally conductive sleeve made from metal, metal-matrix composite (MMC) materials, also referred to as metal-matrix material. The barrel core and barrel sleeve may include aligning features to prevent separation and movement of the sleeve along the core. The disclosed methods provide for material combinations and part designs that prevent separation of their parts over the life of the weapon barrel and allow the barrel to perform at high cadence over the whole temperature range the barrel is used.

Abstract: Disclosed herein is an inflow cannula for an implantable blood pump assembly. The inflow cannula includes a tubular body that extends from a proximal end to a distal end. The tubular body includes a proximal portion adapted for connection to a pump housing, and a distal portion adapted for positioning within an opening formed in a heart. The inflow cannula further includes an expandable sleeve coupled to an exterior surface of the distal portion. The sleeve has a first portion coupled to the distal portion of the tubular body, and a second portion extending from the distal end of the tubular body. The second portion is deployable from a first, stored configuration to a second, deployed configuration in which the second portion expands radially to engage and conform to an endocardial surface of the heart.

Abstract: A weapon barrel has a barrel core composed of iron or nickel alloy and at least one barrel jacket made from a metal-matrix material encasing the barrel core. The jacket and core thereby form a metal-metal-matrix composite barrel. The metal-matrix material may have a specific tensile strength that is greater than or equal to 80 N·m/g, and greater than or equal to the specific tensile strength of the barrels core material. The metal matrix material may include aluminum, titanium, beryllium and magnesium alloys, and composites, in addition to a filler material such as carbon nanotubes, graphite, diamond, carbides, and nitrides.

Abstract: A weapon barrel has a barrel core composed of iron or nickel alloy and at least one barrel jacket made from a metal-matrix material encasing the barrel core. The jacket and core thereby form a metal-metal-matrix composite barrel. The metal-matrix material may have a specific tensile strength that is greater than or equal to 80 N·m/g, and greater than or equal to the specific tensile strength of the barrels core material. The metal matrix material may include aluminum, titanium, beryllium and magnesium alloys, and composites, in addition to a filler material such as carbon nanotubes, graphite, diamond, carbides, and nitrides.

Abstract: The invention is directed to the construction of weapon barrels from a steel core and at least one metal-matrix material sleeve, forming a composite metal-metal-matrix barrel which are applicable in rifles, shotguns, cannons, and mortars. Due to the properties of the metal-matrix materials (e.g. higher specific strength, higher specific heat capacity and lower density), the composite barrels can exhibit a higher rate of fire, reduced weight, improved accuracy, or a combination of any of these properties. Disclosed are various exemplary embodiments of such barrels with improved performance, properties of the metal-matrix materials necessary to allow these improvements as well as methods to produce the same.

Abstract: The invention is directed to the construction of weapon barrels from a steel core and at least one metal-matrix material sleeve, forming a composite metal-metal-matrix barrel which are applicable in rifles, shotguns, cannons, and mortars. Due to the properties of the metal-matrix materials (e.g. higher specific strength, higher specific heat capacity and lower density), the composite barrels can exhibit a higher rate of fire, reduced weight, improved accuracy, or a combination of any of these properties. Disclosed are various exemplary embodiments of such barrels with improved performance, properties of the metal-matrix materials necessary to allow these improvements as well as methods to produce the same.

Abstract: A band and buckle for wrapping around and/or securing one or more objects is provided. Specifically, the band is adapted to receive external objects and maintain the received external objects within the band. The external objects may include electronic devices, sensors, Radio Frequency Identification (RFID) devices or other similar objects. These objects may be used for identifying the objects that are secured by the band, determining information about the band or its surrounding, and other various functions.

Abstract: A spacecraft with a reaction wheel system can be autonomously safed by setting the solar wings to continuous tracking, determining a slew rate vector based on the total angular momentum, and slewing the spacecraft using the slew rate vector until commanded to stop autonomous safing. When the total angular momentum of the spacecraft to large to be handled by rotisserie, then the spacecraft is reoriented to align a suitable rotation vector with the system momentum. In a typical application, the spacecraft has a reaction wheel assembly with four wheels arranged to form a right regular pyramid. Two reaction wheels on opposite edges of the pyramid form a first pair and the two remaining reaction wheels forming a second pair.

Abstract: A spacecraft with a reaction wheel system can be autonomously safed by setting the solar wings to continuous tracking, determining a slew rate vector based on the total angular momentum, and slewing the spacecraft using the slew rate vector until commanded to stop autonomous safing. When the total angular momentum of the spacecraft to large to be handled by rotisserie, then the spacecraft is reoriented to align a suitable rotation vector with the system momentum. In a typical application, the spacecraft has a reaction wheel assembly with four wheels arranged to form a right regular pyramid. Two reaction wheels on opposite edges of the pyramid form a first pair and the two remaining reaction wheels forming a second pair.