Abstract: An electric tandem rotorcraft is disclosed. The tandem rotorcraft can include a forward and an aft electric rotor assembly operably coupled to a fuselage of the rotor craft. The aft rotor assembly can be coupled to the fuselage via a tail structure. The rotorcraft can include a wing assembly that can be operably rotatable between a vertical lift configuration and a horizontal flight configuration. The wing assembly can be disposed between and/or below planes of rotation of the forward and aft rotor assemblies. The forward and aft rotor assemblies can have planes of rotation that overlap one another and may or may not intermesh. The forward and aft rotor assemblies can also be distanced such that their respective planes of rotation do not overlap.

Abstract: A tandem tiltrotor aircraft in which the tiltrotor assemblies are operably coupled at the forward and aft ends of the fuselage of the aircraft is disclosed. The tiltrotor assemblies are capable of rotating between a vertical lift position and a horizontal flight position. The in-line location of the tiltrotor assemblies allow the aircraft to have the vertical take-off and landing capabilities, and, in combination with the at least one wing, can be used in horizontal flight. The aft rotor assembly can assume a horizontal flight position that places the rotor blades forward of a vertical fin of the aircraft. In another embodiment, a winged triple tiltrotor aircraft is disclosed. In another embodiment, a winged quad tiltrotor aircraft is disclosed.

Abstract: A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.

Abstract: Oil-injected screw compressor installation including a frame or underframe (5 2), a screw compressor element (3), electrical cabinet (6), oil separator vessel (5) and an air-cooled cooling module (8), with as characteristic that on one side (2a) of the frame (2), the screw compressor element (3) is placed horizontally and with the electrical 10 cabinet (6), the oil separator vessel (5) and the aircooled cooling module (8) being placed on the other side (2b) of the frame (2), with the cooling module (8) being placed such that this is perpendicular to the compressor element (3) and the air (9) sucked in by the cooling module 15 (8) will flow between the electrical cabinet (6) and the cooling module (8).

Abstract: A support jig for use with a testing machine applying tensile loads, the support jig includes a frame and a pair of spaced apart supports joined to the frame to provide an alignment axis. Each support is configured to releasably hold a test specimen holder on the alignment axis in a fixed spatial relationship with ends of the test specimen holders mountable to the test machine facing in opposite directions. A method of using the support jig to remotely mount the test specimen to the test specimen holders from the test machine, and then using the support jig to maintain the fixed special relationship while the test specimen holders are mounted to the test machine is also provided.

Abstract: Described herein are compositions composed of micronized placental components and pharmaceutical compositions thereof. The compositions have numerous medical applications. Methods for making and using the micronized compositions are also described herein.

Abstract: Described herein are compositions composed of micronized placental components and pharmaceutical compositions thereof. The compositions have numerous medical applications. Methods for making and using the micronized compositions are also described herein.

Abstract: A hybrid propulsion engine for a rotorcraft includes a core turboshaft engine having a gas path and an output shaft that provides torque to a main rotor. A fan module is disposed relative to the core turboshaft engine and is coupled to the output shaft. The fan module has a bypass air path that is independent of the gas path. A thrust nozzle is configured to mix exhaust gases from the core turboshaft engine with bypass air from the fan module and to discharge the mixture to provide propulsive thrust. In a turboshaft configuration, the fan module is closed to prevent the flow of bypass air therethrough such that the thrust nozzle does not provide propulsive thrust. In a turboshaft and turbofan configuration, the fan module is open allowing the flow of bypass air therethrough such that the thrust nozzle provides propulsive thrust, thereby supplying propulsion compounding for the rotorcraft.

Abstract: A method of controlling spread pattern of a particulate material broadcasted by a spinner spreader involves permitting particulate material to flow through a plurality of sluices situated in a particulate material path between a bin and a rotatable disc of a spinner spreader. Each sluice receives a portion of the particulate material and delivers the portion of particulate material to a radial and/or angular position on the rotatable disc. The radial and/or angular position on the rotatable disc to which the portion of particulate material from at least one of sluices is delivered is adjusted by longitudinally translating the at least one independently moveable sluice independent of all other sluices of the plurality of sluices to change position of the at least one independently moveable sluice relative to the rotating disc thereby changing the spread pattern of the particulate material broadcasted by the rotatable disc.

Abstract: Described herein are compositions composed of micronized placental components and pharmaceutical compositions thereof. The compositions have numerous medical applications. Methods for making and using the micronized compositions are also described herein.

Abstract: Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.

Abstract: Described herein are compositions composed of micronized placental components and pharmaceutical compositions thereof. The compositions have numerous medical applications. Methods for making and using the micronized compositions are also described herein.

Abstract: Open-cell foam having a structure of interconnected struts formed of polymeric material and defining open cells, resulting from polymerization of a continuous phase of a high internal phase water-in-oil emulsion, the struts comprising the polymeric material with clay nanoparticles at least partially captured therewithin, is disclosed. The clay nanoparticles may be present in combination with a surface modifier. Methods for making the open-cell foam are also disclosed. Absorbent articles including the open cell foam are also disclosed.

Abstract: A longitudinally adjustable flow divider situated in the particulate material path of a spinner spreader between the bin and the rotatable disc divides the particulate material so that the particulate material is dischargeable on to the upper surface of the rotatable disc on first and second laterally spaced apart longitudinally oriented drop lines. An actuator operably connected to the flow divider adjusts a longitudinal position of the flow divider to longitudinally adjust drop points on the drop lines at which the particulate material is dischargeable on to the rotatable disc. Longitudinal adjustment of the drop points along laterally spaced apart drop lines on one spinner disc permits control over spread pattern to help achieve uniform distribution of the particulate material on a ground surface.

Abstract: An apparatus for spreading particulate material has a bin for holding particulate material, a rotatable disc for broadcasting the particulate material to a ground surface, a conveyor for conveying the particulate material in a particulate material path from the hopper to the rotatable disc, and a plurality of sluices situated in the particulate material path between the bin and the rotatable disc. Each sluice receives a portion of the particulate material and delivers the portion of particulate material to a radial and/or angular position on the rotatable disc. At least one of the sluices is independently moveable to adjust the radial and/or angular position on the rotatable disc to which the portion of particulate material from the at least one independently moveable sluice is delivered.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes first and second engines, a binary lift fan system, first and second forced air bypass systems and first and second exhaust systems. The engines have turboshaft and turbofan modes. The lift fan system includes ducted fans in a tandem longitudinal orientation. In the VTOL orientation of the aircraft, the engines are in the turboshaft mode coupled to the lift fan system such that the engines provide rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engines are in the turbofan mode coupled to the forced air bypass systems such that the bypass air combines with the engine exhaust in the exhaust systems to provide forward thrust generating the wing-borne lift.

Abstract: A paddle tine for use over a pickup tine previously fixed with a harvester reel tube of a harvesting header comprises an elongated body having a central cavity therethrough and is adapted to slide over the pickup tine of the harvester reel tube. An attachment mechanism, such as one or more resilient clips with a fastening clip, is fixed with the proximal end of the elongated body to secure the paddle tine to the harvester reel tube over the pickup tine. Two opposing paddle webs project laterally away from the elongated body proximate the distal end.

Abstract: A personal care composition is disclosed comprising abrasive particles. The personal care composition may take a variety of forms such as a leave-on composition or an emulsion and/or may comprise one or more actives or agents.

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The aircraft has a blended wing body and includes an engine, a trinary lift fan system, a forced air bypass system and an exhaust system. The engine has a turboshaft mode and a turbofan mode. The lift fan system includes a plurality of ducted fans in a tandem lateral and forward orientation. In the VTOL orientation of the aircraft, the engine is in the turboshaft mode coupled to the lift fan system such that the engine provides rotational energy to the ducted fans generating the thrust-borne lift. In the forward flight orientation of the aircraft, the engine is in the turbofan mode coupled to the forced air bypass system such that bypass air combines with engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.