Abstract: A medical device, configured to perform an endovascular therapy, e.g., thrombectomy, can comprise an elongate manipulation member having a first connection member proximate a distal end of the elongate manipulation member, and an intervention member having a second connection member proximate a proximal end of the intervention member. The second connection member can be connected to the first connection member such that the first connection member can rotate relative to the second connection member.

Abstract: An aircraft power plant, has: a combustion engine having an outlet outputting combustion gases; a turbine downstream of the combustion engine; a detonation combustion tube fluidly connecting the combustion engine to the turbine; a member having an open position in which the outlet of the combustion engine is fluidly connected to the turbine and a closed position in which the combustion engine is fluidly disconnected from the turbine; a fuel injector fluidly connected to the detonation combustion tube; an igniter operatively connected to the detonation combustion tube; and a controller operatively connected to the fuel injector and to the igniter, the controller configured to, in response to receiving of a command: inject fuel into the detonation combustion tube via the fuel injector, and once the member is in the closed position, power the igniter to ignite a mixture of the combustion gases and the fuel into the detonation combustion tube.

Abstract: Retrieval of material from vessel lumens can be improved by electrically enhancing attachment of the material to the thrombectomy system. The system can include a catheter having a distal portion configured to be positioned adjacent to a thrombus in a blood vessel, an electrode disposed at the distal portion of the catheter, and an interventional element configured to be delivered through a lumen of the catheter. The electrode and the interventional element are each configured to be electrically coupled to an extracorporeal power supply.

Abstract: There is provided a power generation system for recuperating waste heat in an aircraft power plant. The power generation system includes a source of ammonia; an ammonia cracker in fluid communication with the source and decomposing the ammonia into hydrogen and nitrogen; a separator in fluid communication with the ammonia cracker, the separator separating the hydrogen and nitrogen from the ammonia cracker, the separator having a first outlet for a first output including hydrogen and a second outlet for a second output including hydrogen and nitrogen; a fuel cell in fluid communication with the first outlet of the separator, the fuel cell using the hydrogen of the first output of the separator and an oxidizing agent to generate electrical energy; and a thermal engine in fluid communication with the second outlet of the separator, the thermal engine using the hydrogen of the second output of the separator to generate mechanical energy.

Abstract: A system is provided for an aircraft. This aircraft system includes a nacelle, an aircraft component, an aircraft propulsion system and an electric compressor. The aircraft component is arranged outside of the nacelle. The aircraft propulsion system includes a propulsor rotor and a powerplant configured to drive rotation of the propulsor rotor. The powerplant is housed within the nacelle. The electric compressor is housed within the nacelle and is fluidly discrete from the powerplant. The electric compressor is fluidly coupled with and is configured to provide compressed air to the aircraft component.

Abstract: An aircraft engine oil distribution system includes a system container, an oil reservoir disposed in the system container, the oil reservoir having a plurality of fins protruding from an inner-surface of a wall of the oil reservoir and extending into the oil reservoir, and a heat exchanger disposed in the system container. The heat exchanger includes a cooling fluid passage defined at least between the one or more walls of the system container and the sidewall of the oil reservoir, a matrix disposed in the cooling fluid passage in heat transfer relationship with the plurality of fins of the oil reservoirs.

Abstract: An electric aircraft engine includes an electric motor driving a propulsor. A power source powers the electric motor. An electric compressor supplies compressed air. A nacelle surrounds the electric motor, the power source and the electric compressor. An aircraft and a method are also disclosed.

Abstract: A system is provided for an aircraft. This system includes a propulsor rotor and a powerplant configured to drive rotation of the propulsor rotor. The powerplant includes a turbo-compounded intermittent internal combustion engine and a dual rotor electric machine. The turbo-compounded intermittent internal combustion engine includes a turbine rotor operatively coupled to the propulsor rotor through the dual rotor electric machine. The dual rotor electric machine includes a first rotor, a second rotor, a first stator and a second stator. The first stator and the second stator are arranged radially between and axially aligned with the first rotor and the second rotor.

Abstract: A reclining chair is described that includes a backrest, a seat, and a frame. The backrest and the seat are attached to the frame. The backrest pivotally couples to the frame about a fixed axis. The seat slidingly couples to the frame about a seat axis. The backrest and the seat rotatably couple to one another about a floating axis. The reclining chair is moveable between an upright position and a fully reclined position.

Abstract: An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.

Abstract: A method of manufacturing an apparatus for fixing bone includes mating a first plate with a second plate, where the first plate includes a screw slot and the second plate includes a through hole corresponding to the screw slot; and placing a screw body into the screw slot and the through hole. The screw body includes a screw portion and an insertion portion. The screw body is placed into the screw slot using the insertion portion of the screw body. The method further includes removing the insertion portion of the screw body. The screw portion remains within the screw slot and the through hole after the insertion portion is removed.

Abstract: An aircraft system is provided that includes a first propulsor rotor, a second propulsor rotor and an electric machine. The first propulsor rotor is rotatable about an axis. The second propulsor rotor is rotatable about the axis. The electric machine includes a first electric machine rotor, a second electric machine rotor and an electric machine stator radially between the first electric machine rotor and the second electric machine rotor. The first electric machine rotor is rotatable about the axis and rotatably connected to the first propulsor rotor. The first electric machine rotor and the electric machine stator form a first motor configured to drive rotation of the first propulsor rotor. The second electric machine rotor are rotatable about the axis and rotatably connected to the second propulsor rotor. The second electric machine rotor and the electric machine stator form a second motor configured to drive rotation of the second propulsor rotor.

Abstract: An aircraft power plant, has: a combustion engine having an outlet outputting combustion gases; a turbine downstream of the combustion engine; a detonation combustion tube fluidly connecting the combustion engine to the turbine; a member having an open position in which the outlet of the combustion engine is fluidly connected to the turbine and a closed position in which the combustion engine is fluidly disconnected from the turbine; a fuel injector fluidly connected to the detonation combustion tube; an igniter operatively connected to the detonation combustion tube; and a controller operatively connected to the fuel injector and to the igniter, the controller configured to, in response to receiving of a command: inject fuel into the detonation combustion tube via the fuel injector, and once the member is in the closed position, power the igniter to ignite a mixture of the combustion gases and the fuel into the detonation combustion tube.

Abstract: A method is provided for manufacturing an engine component. During this method, a preform engine component is provided that includes a substrate. The substrate includes a substrate surface and a plurality of apertures. Each of the apertures projects partially into the substrate from the substrate surface. A coating is formed on the substrate. The coating includes a base and a plurality of projections. The base covers the substrate surface. Each of the projections projects out from the base into and fills a respective one of the apertures. The forming of the coating includes electroless plating a coating material onto the substrate over the substrate surface and within the apertures.

Abstract: Retrieval of material from vessel lumens can be improved by electrically enhancing attachment of the material to the thrombectomy system. The system can include a catheter having a distal portion configured to be positioned adjacent to a thrombus in a blood vessel, an electrode disposed at the distal portion of the catheter, and an interventional element configured to be delivered through a lumen of the catheter. The electrode and the interventional element are each configured to be electrically coupled to an extracorporeal power supply.

Abstract: Convertible furniture includes a first arm, a first seat, and a base. The first seat is adjacent the first arm and includes a head panel, a mid-panel, and a foot panel. The first seat has a seat configuration in which the head panel is in a vertical orientation. The first seat has a bed configuration in which the head panel, the mid-panel, and the foot panel are each in a horizontal orientation with a top surface of each cooperating to form a flat surface. The base has a side rail that is secured to the first arm and a center support parallel to and spaced apart from the first arm. The head panel of the first seat at least partially supported by the side rail and the center support in the deployed position thereof when the first seat is in the bed configuration.

Abstract: Retrieval of material from vessel lumens can be improved by electrically enhancing attachment of the material to the thrombectomy system. The system can include a catheter having a distal portion configured to be positioned adjacent to a thrombus in a blood vessel, an electrode disposed at the distal portion of the catheter, and an interventional element configured to be delivered through a lumen of the catheter. The electrode and the interventional element are each configured to be electrically coupled to an extracorporeal power supply.

Abstract: Retrieval of material from vessel lumens can be improved by electrically enhancing attachment of the material to the thrombectomy system. The system can include a catheter having a distal portion configured to be positioned adjacent to a thrombus in a blood vessel, an electrode disposed at the distal portion of the catheter, and an interventional element configured to be delivered through a lumen of the catheter. The electrode and the interventional element are each configured to be electrically coupled to an extracorporeal power supply.

Abstract: An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.