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

Abstract: An aerial resupply system (ARS) including a supply aircraft. The supply aircraft includes at least one of supply fuel, an ordinance, and data. The supply aircraft also includes a retractable boom system (RBS) configured for selective stowage within a fuselage of the supply aircraft and configured to supply at least one of supply fuel, the ordinance, and data to a location external to the fuselage.

Abstract: A rotorcraft has a fuselage, an engine disposed substantially laterally centrally relative to the fuselage, and an air intake system (AIS). The AIS has a first duct configured to provide streamline air flow, a second duct configured to provide streamline air flow, and a combining section configured to receive streamline air flow from each of the first duct and the second duct. The combining section is further configured to output streamline air flow.

Abstract: A modal tailboom flight control system for a compound helicopter is operable in a plurality of modes including a forward thrust mode and an anti-torque mode. The modal tailboom flight control system includes a tailboom, a drivetrain extending through the tailboom, an anti-torque system coupled to the drivetrain and rotatable to generate anti-torque thrust for the compound helicopter in the anti-torque mode and a pusher propeller coupled to the drivetrain and rotatable to generate forward thrust for the compound helicopter in the forward thrust mode. The pusher propeller is positioned forward of the anti-torque system.

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: 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: Oil-injected screw compressor installation including a frame or underframe (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 cabinet (6), the oil separator vessel (5) and the air-cooled 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 (8) will flow between the electrical cabinet (6) and the cooling module (8).

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: 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: A pylon assembly for a tiltrotor aircraft includes a rotor assembly rotatably coupled to a fixed pylon and operable to rotate between a vertical takeoff and landing orientation and a forward flight orientation. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension is rotatably disposed to the outboard end of the fixed pylon such that the rotor assembly and the wing extension are separated by at least a portion of the fixed pylon. The wing extension has a forward edge and an outboard end. A winglet is coupled to the outboard end of the wing extension and has a forward edge. The wing extension and the winglet are configured to rotate in synchrony with the rotor assembly such that the forward edges of the wing extension and the winglet remain in the slipstream of the proprotor.

Abstract: Various implementations described herein are directed to a vertical takeoff and landing system. In one implementation, the vertical takeoff and landing system includes a carriage. The carriage includes a thrust component configured to provide vertical and/or horizontal thrust for the carriage and one or more housings configured to receive an aircraft in a joined configuration of the carriage and the aircraft.

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 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: 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: Additively manufactured ceramic filters are disclosed. A plurality of pores, each having a uniform geometry, arc arranged between an inlet surface and an outlet surface of a single unit of ceramic such that the plurality of pores change in size uniformly from the inlet surface to the outlet surface. The pores are respectively interconnected, and the size, shape, orientation, and/or interconnection of the pores are chosen to provide hydrodynamic features that provide effective filtration for a given liquid and contamination. The pores are additively manufactured with optimized precision.

Abstract: A method for polymerizing an open-cell foam including exposing an emulsion comprising a photoinitiator to an Ultraviolet light source, partially polymerizing the top surface of the emulsion, and moving the partially polymerized emulsion to a second polymerization stage.

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 modal tailboom flight control system for a compound helicopter is operable in a plurality of modes including a forward thrust mode and an anti-torque mode. The modal tailboom flight control system includes a tailboom, a drivetrain extending through the tailboom, an anti-torque system coupled to the drivetrain and rotatable to generate anti-torque thrust for the compound helicopter in the anti-torque mode and a pusher propeller coupled to the drivetrain and rotatable to generate forward thrust for the compound helicopter in the forward thrust mode. The pusher propeller is positioned forward of the anti-torque system.