Abstract: A cantilevered canopy structure includes at least one vertical support having a first and second upper support joint. The structure further includes at least one first and second horizontal support. The first horizontal support is affixed to the vertical supports at the first upper support joint. The second horizontal support is affixed to the vertical supports at the second upper support joint. The structure further includes cantilever supports. The cantilever support is affixed to the first and second horizontal supports. The structure further includes at least one horizontal frame member. The horizontal frame member is affixed to the cantilever supports at a cantilever frame joint. The first upper support joint is located higher than the second upper support joint. The first upper support joint and second upper support joints are distal, in opposing directions, from the vertical support.

Abstract: A bearing system including a wheel assembly transmitting load to a damping assembly, wherein the wheel assembly is configured to rotate angularly relative to the damping assembly.

Abstract: An unmanned surface vehicle (USV) including a main body; a slideway; and an automatic recovery unit. The slideway includes pulleys, slide rails, sleepers, end plates disposed at two sides of the sleepers, and baffle plates. The automatic recovery unit includes a buoy, a connection rod, a downhaul, an electromagnetic fixer, a winch, an upper cable, a storage box, and a recovery net. The slideway is fixed on the afterdeck of the main body and the tail end of the slideway sticks out the side boundary of the afterdeck. The baffle plates are disposed on the upper end of the end plates. The vertical height of the end plates is larger than the maximum vertical height of the pulleys and the slide rails. The baffle plates on the upper end of the end plates limit the displacement of the buoy in the vertical direction.

Abstract: A pontoon boat includes at least two pontoon tubes, a platform supported on the at least two pontoon tubes, and an occupancy compartment capable of containing at least one occupant, the occupancy compartment having a length, a width, an upper portion extending vertically above the platform that includes a ceiling, and a lower portion extending vertically below the platform and into one of the at least two pontoon tubes, the lower portion including a floor surface for supporting the occupant. An entrance to the occupancy compartment is provided in the upper portion that permits the occupant to enter and exit the occupancy compartment.

Abstract: An aquatic vessel basically includes a floating body, a submersible propulsion unit and a communication device. The floating body has an above water level surface and a below water level surface. The submersible propulsion unit is disposed on the floating body beneath the below water level surface of the floating body. The communication device is disposed on the floating body above the above water level surface of the floating body. The communication device is wired to the submersible propulsion unit, and is configured to wirelessly communicate with a control module.

Abstract: The invention relates to a system for actively damping a ship's motion, comprising at least one first rotatable stabilization element extending from the ship's hull, below the water line, on a side of the ship, sensor means for sensing the ship's motion and delivering control signals on the basis thereof to driving means for rotatably driving the stabilization element for the purpose of damping the ship's motion being sensed, as well as moving means for moving the stabilization element relative to the ship. According to the invention, the active stabilization system is to that end characterized in that the moving means are configured to impart a precession motion to the at least one rotatable stabilization element in dependence on the ship's sailing speed and the control signals being delivered by the sensor means. Imparting a precession movement to the rotating stabilization elements obviates the need to constantly change the direction of the mass of the stabilization elements.

Abstract: A method for providing lighting to a boat surface comprising providing an LED light source in a transparent disk and placing the disk on the boat surface in a location where the seat pedestal is to be mounted with the disk fastener openings aligned with the boat surface openings. The method includes connecting a power source to the light source, placing the seat pedestal on the transparent disk with the seat pedestal fastener openings aligned with the disk fastener openings and inserting the at least one fastener through the seat pedestal openings, disk openings and boat surface openings. The fastener secures the seat pedestal and disk to the boat surface wherein the transparent disk bears the weight of the seat pedestal. Upon providing power to the light source, light travels from the light source to the circumferential edge of the transparent disk, illuminating the area adjacent the seat pedestal.

Abstract: A spacing component comprising a longitudinal axis wherein the structural spacing component may be configured to provide a boundary between a first object and a second object along its longitudinal axis is described. The structural spacing component may further comprise a restrictive layer enclosing an interior region wherein the restrictive layer may comprise a first length along the longitudinal axis and at least one second length transverse to the longitudinal axis. In examples, the restrictive layer may be formed of a plurality of braided strands. Additionally, the restrictive layer may define at least a partially enclosed interior region and may have flexural stiffness to maintain the first length as greater than the second length.

Abstract: The invention provides an element (210) comprising: (i) an electrical component (1220); (ii) an optical medium (270) comprising medium material (275) comprising a silicone transmissive for one or more of UV radiation and visible radiation, wherein the electrical component (1220) is embedded in the optical medium (270); (iii) an electrical connector (510) for functionally coupling the electrical component (1220) external to the optical medium (270), wherein the electrical connector (510) is embedded in the optical medium (270) over at least part of its length; and (iv) a water barrier (530) at least partly embedded in the optical medium (270) and configured to enclose at least part of the electrical connector (510).

Abstract: A marine structure including a floating deck attached to a damper configured to control the vertical movement of the deck. The damper allows vertical motion of the floating deck in response to gradual changes in water level such as tidal changes, but resists bouncing of the deck in response to shorter term fluctuations in water level such as boat wakes or wind chop.

Abstract: New expanding net interceptors and rescue devices are provided. In some aspects of the invention, a rescue device comprises a dense, positionable head, an extendable boom and a handle with an expansion and/or inflation trigger, wherein the positionable head comprises folded or compacted net, expandable and/or inflatable by the expansion and/or inflation trigger.

Abstract: A waterproof seal includes a flexible annular tube formed by an inner layer and an outer layer of a garment and surrounding a passage through which a human appendage is intended to protrude. A first cord is positioned in a cavity defined by the annular tube. The first cord has a first end, a second end and extends more than 180 degrees and less than 360 degrees around the passage with the first end and the second end exiting the annular tube. A second cord is positioned in the cavity defined by the annular tube. The second cord has a first end, a second end and extends more than 180 degrees and less than 360 degrees around the passage with the first end and the second end exiting the annular tube. The first cord and the second cord cumulatively cover more than 360 degrees around the passage to provide an effective water seal.

Abstract: A carbon dioxide cycle power generation system includes storage collectively storing portions of carbon dioxide liquid and gas and a transfer connection selectively directing flow of the carbon dioxide through a turbine. The system cycles between different seawater depths in order to employ at least one of seawater pressure and seawater temperature in creating the carbon dioxide flow. Inlet/outlet control valves on variable volume tanks, positioned below movable pistons within the respective tank, selectively allow seawater into or out of a lower portion of the respective tank below the piston to pressurize the carbon dioxide therein relative to the carbon dioxide within the other tank when at depth rather than near the surface. Inhibited versus uninhibited heat transfer between storage portions and the seawater allows different seawater temperatures at depth and near the surface to create the carbon dioxide flow. Acoustic communications may be driven concurrent with the turbine.

Abstract: An example underwater vehicle includes a first section detachably coupled to a second section that is positioned forward of the first section, and a hinge detachably coupling the first section to the second section, where the hinge creates a pivot between the first section and the second section. The underwater vehicle includes a lock having a locked position and an unlocked position, where, in the locked position, the lock couples the first section and the second section together, and where, in the unlocked position, the second section is capable of decoupling from the first section. The underwater vehicle also includes a drag fin associated with the second section that is movable to an extended position away from the second section to create a drag force which causes the second section to pivot about the hinge, away from the first section, when the underwater vehicle is traveling through a fluid medium.

Abstract: A watercraft immobilizing apparatus and system for a marine vessel to passively defend against an attacking engine-powered watercraft includes a towed array of entanglement lines. The entanglement lines can be provided on and administered from reusable/removable/replaceable storage cartridges mountable on a hull mount or stowed in a watertight chamber in the vessel's hull, and/or deployed via floated booms and/or paravanes to foul and immobilize propellers and engine cooling water intakes of encroaching watercraft.

Abstract: A fuel cell watercraft includes: a hull; an electric motor serving as a power source adapted to generate propulsion of the hull; a fuel cell unit adapted to supply electric power to the electric motor; a hydrogen fuel tank adapted to supply hydrogen fuel to the fuel cell unit; a secondary battery serving as an auxiliary power supply for the fuel cell unit; and power regulation means for regulating the electric power supplied to the electric motor, in which the hull includes first and second storage spaces isolated from each other, the first and second storage spaces include equipment hatches able to be opened and closed by lid members, the fuel cell unit and the hydrogen fuel tank are housed in the first storage space, and the secondary battery and the power regulation means are housed in the second storage space.

Abstract: A marine propulsion unit is described. The marine propulsion unit allows for shallow, obstructed, or otherwise impeded operation of a vessel through a novel marine propulsion transfer unit that is, or can be, mechanically coupled to an outboard motor or other similar marine motor. A mount for raising and lowering the marine propulsion unit in a generally vertical direction allows for adjustment of operating depth of the marine propulsion unit to accommodate a wide range of operating conditions from shallow and obstructed water to traditional deep water operation.

Abstract: When a main switch is turned on, a main relay is energized so as to supply electric power to a computer system; when an engine starting switch is turned on, an engine is started and energization of the main relay is continued; when an engine stopping switch is turned on, the engine is stopped, and the main relay is de-energized so as to stop supply of electric power to the computer system.

Abstract: An exhaust system for a marine exhaust system includes two identical liquid-cooled exhaust manifolds. Each exhaust manifold has an outlet portion adapted to receive and retain a catalytic converter. Liquid cooled first and second risers are secured to the first and second exhaust manifolds. Bypass hoses enable fluid to pass from each exhaust manifold to its coupled riser. At the outlet of each riser, the cooling fluid and exhaust gas mix in a Y-pipe to create a combined flow. An exhaust outlet conduit downstream of the Y-pipe receives the combined flow and discharges the combined flow.

Abstract: A ship including a storage tank for storing a liquefied gas includes: a boil-off gas (BOG) heat exchanger installed on a downstream of a storage tank and heat-exchanges a compressed BOG (“a first fluid”) by a BOG discharged from the storage tank as a refrigerant, to cool the BOG; a compressor installed on a downstream of the BOG heat exchanger and compresses a part of the BOG discharged from the storage tank; an extra compressor installed on a downstream of the BOG heat exchanger and in parallel with the compressor and compresses the other part of the BOG discharged from the storage tank; a refrigerant heat exchanger which additionally cools the first fluid cooled by the BOG heat exchanger; and a refrigerant decompressing device which expands a second fluid sent to the refrigerant heat exchanger, and then sends the second fluid back to the refrigerant heat exchanger.

Abstract: A multilayer floor covering includes a layer A of reinforcing fibers, an adhesive layer B, an underside layer C, a reinforcing layer D, free of reinforcing fibers, made of thermoplastic polymer chosen from the group comprising polyester resins, acrylic resins and mixtures thereof, and a surface layer E.

Abstract: An aerodynamic structure incorporated in an aircraft control surface (10) provides a spar (16) extending along at least a portion of the control surface in a direction and the spar includes a plurality of bends along the direction of extension along the control surface to provide space to accommodate actuator fittings or other structural or operational requirements.

Abstract: A method of bonding two components at a joint interface using a UV-curable substance. The method comprises incorporating a UV radiation emitting device in the joint interface between the components together with said substance and supplying power to said UV radiation emitting device to generate UV radiation and cure the substance.

Abstract: The present invention relates to structural component for an aircraft. The structural component comprises a body with a first surface and a lug that extends out of the first surface. The body and lug comprise a composite material and are integrally formed.

Abstract: A coupling device for supporting a first wing section against a second wing section of an aircraft, and configured for passive flight load alleviation includes a housing including a chamber including a first portion and a second portion and filled with a fluid, a piston device movably arranged in the chamber and separating the first portion from the second portion in a fluid tight manner, a first fluid pathway connecting the first portion to the second portion, a first pressure relief valve arranged in the first fluid pathway and blocking the first fluid pathway, if the pressure in the second portion is smaller than a first relief pressure and opening the first fluid pathway, if the pressure in the second portion is greater than the first relief pressure. In addition, the coupling device can be used to actuate the second wing section against the first wing section.

Abstract: This invention relates to an aircraft flap mechanism, entirely contained within each flap, such that each flap can be activated independently of any other. The mechanism includes electric, pneumatic or hydraulic motors which activate the movement of the flaps. The invention results in a compact, light, low cost, reliable and easy to maintain mechanism. Furthermore, due to the fact that the mechanism is entirely contained within the flap it maximizes internal wing space.

Abstract: A pitch change mechanism for a bladed rotor includes a driving sleeve, a drive shaft, a first pitch-changing element, a second pitch-changing element, and a plurality of blade drive gears. The driving sleeve has, in axial sequence, a first helical connection portion and a second helical connection portion. The driving sleeve is positioned concentrically with and surrounding the drive shaft. The first pitch-changing element has a first end drivingly engaged with the first helical connection portion, and a first ring gear portion at a second opposite end, while the second pitch-changing element has a first end drivingly engaged with the second helical connection portion, and a second ring gear portion at a second opposite end. The plurality of blade drive gears are arranged in a circumferential array around a longitudinal axis of the drive shaft.

Abstract: An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A stabilizer assembly and a boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The stabilizer assembly includes a stabilizer and a root fillet extending between the stabilizer and the fuselage. The root fillet defines a flow directing surface configured for urging a flow of boundary layer air upward along the vertical direction. In addition, an airflow modifying element may protrude from a surface of the fuselage or the root fillet, the airflow modifying element being configured for directing or reducing swirl in the flow of boundary layer air.

Abstract: An aircraft landing gear assembly includes a lock link and a rotary electromechanical actuator which includes motor and gearbox unit arranged to move a pawl into contact with the lock link to break the lock link. A release mechanism is provided to enable the lock link to be made in the event of the motor and gearbox unit jamming.

Abstract: An aircraft having an airframe that extends longitudinally along an anteroposterior plane. A buoyancy system is provided with at least one pair of two floats arranged transversely on opposite sides of said anteroposterior plane. Each float is movable in elevation from a bottom position to a top position. For each float, the buoyancy system includes a blocking system for blocking each float by default in the bottom position, and for acting under a predetermined condition to block the floats present on one of the sides only of the aircraft in the top position.

Abstract: A multicopter with angled rotors includes a fuselage and a plurality of rotors. At least some of the rotors are disposed on opposite sides of the fuselage and each is oriented at a corresponding angle to a substantially horizontal plane of the aircraft, the angle being of a magnitude such that a plane of rotation of the rotor does not intersect at least a critical portion of the fuselage.

Abstract: Methods, devices, and systems of various embodiments are disclosed for managing an unmanned aerial vehicle (UAV). In various embodiments, the UAV may charge an onboard battery while docked at a docking terminal of a charging station. The UAV may receive a message from the charging station with an instruction to undock from the docking terminal. The UAV may undock from the docking terminal before charging of the onboard battery is complete in response to receiving the message from the charging station with the instruction to undock.

Abstract: A UAV tethering system provides an environment in which to fly an unmanned aerial vehicle (UAV) where the tether is selected to prevent the UAV from unintentional contact with the ground or other objects within the flight area. A tether may connect the UAV to a shuttle that slides along a track. The tether may be used to provide efficient, robust and accurate positioning information. The system can be configured to detect the angle at which the tethering line extends from the shuttle, the length of the extended tethering line, and then compute the position of the UAV relative to the shuttle. Furthermore, by knowing the position of the shuttle, the absolute position of the UAV can be determined.

Abstract: An unmanned autonomous vehicle assessment and reporting system may implement a crisscross boustrophedonic flight pattern for capturing images of a structure to develop a three-dimensional model of the same. Patch scan analysis of predefined sample sizes of the roof may be captured in a separate scan and/or as part of the crisscross boustrophedonic flight pattern. The crisscross boustrophedonic flight pattern may include integrated oblique image captures via structure-facing camera angles during approach portions of each pass of a boustrophedonic flight pattern, via structure-facing end passes, and/or via rounded structure-facing end passes. A crisscross boustrophedonic flight pattern may include two or more boustrophedonic flight patterns that are at angles relative to one another.

Abstract: A lightweight body suit on which a number of high power fan motors are installed. In addition a pair of motors are attached to the user's arms and legs. The combination of fan motors allows adequate lift and the units mounted on the arms and legs allow for controlled flight. The suit also contains a small chest frame for holding batteries and for the protection of the user. In addition, elbow and knee protection are provided. Throttles are provided to control the speed of the motors.

Abstract: A drone for spraying liquid over field crop includes: a frame with a slender rigid beam in the middle and two base structures at the two ends, a rigid tube with an array of nozzles on elongated stems and the rigid tube is suspended below the beam structure with retractable wires, at least three propellers on motors with arms that are rotatably mounted to each of the two base structures of the frame, a power source, at least one distance detector for measuring height, an antenna for communication, an electronic control system to operate motors and sensors, a container for a liquid material and electronic valve to allow liquid in the container to be transferred and sprayed from the nozzles, and a remote controller. The drone is intended to spray liquid over a wide strip of the field with high efficiency, precision, and safety and reduced drift of sprays.

Abstract: Described herein are methods and systems for motorized control of a tether, such as for purposes of user interaction and feedback. In particular, a UAV's control system may determine one or more operational parameters of a motor for a winch disposed in the UAV, the winch including the tether and a spool. The control system may then detect in the one or more operational parameters, an operational pattern of the motor that is indicative of an intentional user-interaction with the tether. Based on the detected operational pattern of the motor that is indicative of the intentional user-interaction with the tether, the control system may determine a motor response process. Then, the control system may operate the motor in accordance with the determined motor response process.

Abstract: A tablet computing device support for use by a user seated on an airplane behind a seat having a folding table. The tablet computing device support comprises a main body, a bottom support element positioned at a bottom end of the main body, at least two lateral support members positioned on opposite sides of the main body, each of the at least two lateral support members including a lateral support element, and at least one securing member configured to be inserted between the folding table in the upright position and the seat in front of the user. The bottom support element and the at least two lateral support elements are configured to receive therebetween and secure a tablet computing device to the tablet computing device support.

Abstract: The invention relates to an overhead luggage compartment for aircraft, comprising: a tray for accommodating pieces of luggage, which tray can be pivoted about an axis of rotation between a closed position and an open position; and comprising a housing, which encloses the tray in the closed position and which has devices arranged thereon for fastening to a supporting structure of the aircraft and has a suspension device for a passenger service unit; and comprising a closure element for holding the tray in the closed position. The housing is formed by two frame parts arranged lateral to the tray, which frame parts are connected to each other by means of cross-braces, and the fastening devices and the suspension device for the passenger service unit and at least one stop element for limiting the open position of the tray are arranged on the frame parts.

Abstract: A table apparatus includes a table device and a table support structure that is connected to the table device. The table support structure includes a carrier structure and a table support linkage. The carrier structure is connected to the table support linkage via a single pivot connection. The table device is pivotable about only the single pivot connection.

Abstract: An electronic module assembly (EMA) for use in controlling one or more personal restraint systems. A programmed processor within the EMA is configured to determine when a personal restraint system associated with each seat in a vehicle should be deployed. In addition, the programmed processor is configured to perform a diagnostic self-test to determine if the EMA and the personal restraint systems are operational. In one embodiment, results of the diagnostic self-test routine are displayed on a display included on the electronic module assembly. In an alternative embodiment, the results of the diagnostic self-test routine are transmitted via a wireless transceiver to a remote device. The remote device can include a wireless interrogator or can be a remote computer system such as a cabin management computer system.

Abstract: Systems and methods are provided for an inductive coil anti-icing and noise absorption system. In certain versions, the inductive coil anti-icing and noise absorption system may include an inductive coil and a skin. The inductive coil may generate electromagnetic fields and may electromagnetically couple with the skin. The skin, upon electromagnetically coupling with the inductive coil, may increase in temperature and the increase in temperature may melt or prevent the formation of ice on the skin. The skin or a portion of the skin may be porous and may allow incorporation of a sound absorbing liner. The sound absorbing liner may attenuate noise generated by the aircraft (e.g., noise generated by the aircraft engine). Certain versions may include a plurality of inductive coils and a plurality of skins.

Abstract: A multicopter aircraft with boom-mounted rotors is disclosed. The multicopter includes a fuselage; a port side wing coupled to the fuselage; and a starboard side wing coupled to the fuselage. Each of the wings has mounted thereto one or more booms, each boom having a forward end extending forward of a corresponding wing to which the boom is mounted and an after end extending aft of said corresponding wing to which the boom is mounted. The aircraft further includes a first plurality of lift rotors, each rotor in said first plurality being mounted on a forward end of a corresponding one or said booms; and a second plurality of lift rotors, each rotor in said second plurality being mounted on an after end of a corresponding one or said booms. Each rotor produces vertical thrust independent of the thrust produced by the other rotors.

Abstract: The disclosure is directed to an optionally hybrid power system that may operate either as a traditional power system, deriving power from a single power source, or as a hybrid power system, deriving power from multiple types of power sources. An example optionally hybrid power system may include a gas turbine engine and one or more electric motors. When configured as a traditional power system the optionally hybrid power system may derive all power from the gas turbine engine. However, when configured as a hybrid power system, the one or more motors may be coupled to the optionally hybrid power system to supplement the power produced by the gas turbine engine. Additionally, an operator interface that may control the optionally hybrid power system may select from a plurality of operating modes that depend on the configuration of the optionally hybrid power system.

Abstract: Propulsion unit for an aircraft, comprising a turbine, at least one propeller offset with respect to the turbine, and a power transmission disposed between the turbine and the propeller, the transmission comprising in series two constant velocity joints with a slide connection.

Abstract: A fuel system for an aircraft includes a fuel cell having a plurality of sides including a first side and at least one deformable clip having a secured end and a free end. The secured end is coupled to the first side of the fuel cell and the free end overlapping the airframe of the aircraft such that the first side of the fuel cell is positioned adjacent to the airframe. The at least one deformable clip is deformable to allow the fuel cell to move independently of the airframe in response to an impact of the aircraft, thereby protecting the fuel cell from damage resulting from the impact.

Abstract: A system for generating inert gas includes a source of pressurized air. An air separation module including at least one permeable membrane is operable to separate the pressurized air into oxygen-enriched air and inert gas-enriched air. A fuel tank containing a fuel is arranged downstream from said air separation module. The inert gas-enriched air output from said air separation module interacts with said fuel to remove dissolved oxygen from said fuel.

Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.

Abstract: An electronic landing platform state module is configured to generate a state estimation of a platform surface at sea includes a plurality of electronic platform state process modules configured to receive an output from a respective spectral sensor. The plurality of electronic platform state process modules are further configured to output a monitored spectral platform state signal in response to applying a spectral process on a respective output. Each spectral process corresponds to a particular spectral modality of the respective spectral sensor. The electronic landing platform state module further includes an electronic platform state estimator module configured to determine a corrected dynamic state of the platform in response to fusing together the individual monitored spectral platform state signals.

Abstract: Passive on-board aircraft cooling systems are provided with an evaporator/receiver in heat-exchange relationship with at least one heat source on board the aircraft, the evaporator/receiver containing a liquid phase working fluid which changes state to a vapor phase working fluid in response to heat transfer therefrom from the at least one heat source. First and second condensers are fluid-connected to the evaporator/receiver for receiving vapor phase working fluid from the evaporator/receiver. At least a portion of the vapor phase working fluid transferred to the first and second condensers is condensed by heat transfer between the first and second condensers and aircraft-external unpressurized and aircraft-internal pressurized air supply streams, respectively, to thereby form liquid phase working fluid which returns to the evaporator/receiver by virtue of the fluid connection with the first and second condensers.