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 mobile line guard apparatus including a movable platform and an articulating support arm mounted to the movable platform. The support arm being upwardly extendable from a stowed position to a height above the movable platform. The support arm can include at least one arm segment and at least one arm actuator positioned between the platform and the arm segment to extend the support arm upwardly from the stowed position. An articulating guard structure can be pivotably coupled to a distal end portion of the support arm. The guard structure can include a base portion, a horizontal beam rotatably coupled to the base portion, a pair of guide rods, each extending at an angle from opposite ends of the horizontal beam, and a guard actuator positioned between the base portion and the distal end portion of the support arm to angle the guard structure with respect the support arm.

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: A cargo transporting system for a tailsitter aircraft includes a cargo receptacle rotatably coupled to an underside of a wing and a cargo assembly selectively coupled to the cargo receptacle. By rotating the cargo receptacle, the cargo transporting system can transition between a deployed position and a retracted position. In the deployed position, the cargo receptacle is substantially perpendicular to the wing, and accommodates ground personnel charged with connecting or removing the cargo assembly from the cargo transporting system. In the retracted position, the cargo receptacle is substantially parallel to the wing, and positioned for flight operations.

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 high speed, vertical lift aircraft that has vertical take-off and landing (VTOL) capability and is capable of converting to a forward-flight mode (e.g., prop-mode). The rotors blades can be folded for high speed forward flight propelled by a turbine engine (e.g., jet-mode). The rotor blades on the tail sitter aircraft have a “stop-fold” capability, which means that the rotor blades are stopped in flight and folded back to reduce drag. This allows the tail sitter aircraft to achieve a higher speed than a tilt-rotor aircraft. In some embodiments, the tail sitter aircraft achieves both rotor-borne flight and jet-borne flight by having two separate engines. An additional advantage of the tail-sitter aircraft versus a horizontally oriented fixed engine aircraft is that supplemental jet thrust can be used for take-off if desired.

Abstract: Disclosed herein are systems, devices, and methods for remotely measuring one or more vital signs of a patient, securely storing and communicating the resulting vital sign data, and configuring the vital sign data for secure access by a healthcare provider computer system to enable remote monitoring of the patients vital signs. One or more vital sign monitoring devices detect patient vital signs and securely transmit the resulting vital sign data to an external computer device such as the patients smart phone or abase station computer device. The external computer device communicates with a server system, such as a secure cloud storage system, which configures the vital sign measurement data and received patient identification data and makes it accessible to one or more healthcare provider computer systems.

Abstract: An aircraft for capturing drones includes an airframe having a drone channel with first and second wings extending outboard thereof. A two-dimensional distributed thrust array includes a plurality of propulsion assemblies coupled to each of the first and second wings such that the rotor disc of each propulsion assembly is outboard of the drone channel. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A mesh bag is coupled to the drone channel forming a drone capture net. The aircraft is configured to convert between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft is also configured to overtake a drone during flight in the biplane orientation such that the drone passes through the drone channel into the mesh bag, thereby capturing the drone in the drone capture net.

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 binary 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 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 the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

Abstract: A propulsion system for an aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a forward flight orientation. The propulsion system includes an turboshaft engine, a 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 at least one ducted fan. 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 at least one ducted fan 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 the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

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 unitary 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 ducted fan. 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 fan 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 the bypass air combines with the engine exhaust in the exhaust system to provide forward thrust generating the wing-borne lift.

Abstract: A drum braking system having a spindle and backing plate affixed thereto. The system includes a drum rotating on the spindle. The drum has an inside surface with integral notches that are machined or cast into the drum. When the brakes are applied, brake shoes are actuated to contact the inside surface to create drag between the drum and the spindle. A sensor is fixed with respect to the spindle or backing plate that detects the notches when the drum rotates about the spindle. A portion of the inside surface with the integral notches is shared with the brake shoes so that applying the brakes prevents buildup that could contact the sensor. The sensor is positioned radially to reduce the effect of drum endplay on detecting of the notches.

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 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: Disclosed herein are systems, devices, and methods for providing continuous, non-invasive blood pressure monitoring. A wearable monitoring device includes first and second transducer arrays separated by a fixed distance. Each of the transducer arrays includes a plurality of independent transducer elements for transmitting and receiving ultrasound energy. When a user wears the device, the transducers are positioned near the brachial artery. The device operates to measure the transit time of a cardiac pulse through the brachial artery and across the fixed distance between transducer arrays. The measured pulse transit time may then be used for determining pulse wave velocity and/or blood pressure.

Abstract: A monitoring system for determining a user's respiration rate includes a wearable monitoring device for attachment to the user's chest wall. The wearable monitoring device includes a plurality of biometric sensors for generating a plurality of separate biometric data types such as motion data, sound data, and EKG data. A controller is included within the wearable monitoring device and/or is communicatively coupled to the device. The controller is configured to receive the biometric data from the biometric sensors, associate the biometric data of each of the separate biometric data types with one another according to a common sampling timeline to generate a set of multiplexed biometric data, and use the multiplexed biometric data to determine the user's respiration rate.

Abstract: Filaments containing a filament-forming material and an additive, such as an ingestible active agent, nonwoven webs, and methods for making such filaments are provided.

Abstract: A nose assembly of an aircraft includes a nose airframe having a nonhorizontal mounting surface and a turret assembly mounted on the nonhorizontal mounting surface. The turret assembly includes a turret device housing rotatable relative to the nonhorizontal mounting surface. The nose airframe includes a nose skin forming a nose fairing having an apex aperture. The nose skin at least partially covers the turret assembly such that the turret assembly is at least partially inset in the apex aperture of the nose fairing.

Abstract: A method of delivering a health care active having the steps of administering to a mammal in need of a health benefit or a treatment for a health condition a personal health care article and consuming the article. The article contains one or more filaments that contain a backbone material, a health care active and optionally aesthetic agents, extensional aids, plasticizers, and crosslinking agents.

Abstract: A canopy for a compressor or generator installation comprising a chassis (2) with—a base plate (3) comprising a body with a mounting surface bounded by a polygonal peripheral edge (4); and—a mounting frame (5) containing this base plate (3) and going around the peripheral edge (4); whereby the canopy (1) further comprises a number of corner stays (6), whereby each corner stay (6) is provided with a mounting end which is configured to be mounted onto the chassis (2), whereby at each corner of the peripheral edge (4), at least one corner stay (6) is mounted with its mounting end onto the chassis (2), whereby each corner stay (6) in a mounted state extends from the mounting surface of the base plate (3) in a direction essentially perpendicular to the mounting surface and outwards from the body of the base plate (3), and whereby each corner stay (6) in a mounted state has a free end which is opposite to the mounting end of this corner stay (6) and which is not mounted onto the mounting surface; and whereby the ca