Abstract: A motorized board similar to a surf board is presented for use on a water surface. The motorized board includes a base board having a front end and a back end, a foot pedal on the base board, wherein the foot pedal is rotatable on the base board, and a motor coupled to the base board and connected to a propeller at the back end, the motor being controlled by the foot pedal. A user can stand on the board and turn the motor on with his foot, as well as control the speed with his foot to ride on a water surface with or without waves.

Abstract: A remote controlled lighted mooring beacon is adapted to be secured to a mooring site. The beacon may include various features, such as a central shaft, a ballast at the base of the shaft containing at least one power source, a float, an electronics package having a receiver that responds to a wireless code for generating an activation signal, and a 360 degree viewable high intensity light source.

Abstract: A safety, rescue, and recovery device that compressively secures to a limb of a user when inflated. The device can be easily adjusted to be negatively buoyant, neutrally buoyant, or positively buoyant before inflation depending on whether the application is safety, rescue, or recovery. The device may also be integrated into an article of clothing for certain applications. An elongated handle is attached to the device to provide a sliding attachment point for a rescue rope that automatically reduces torque applied to the limb of the user. Consequently, a rescue force applied to the rescue rope can act at a variety of angles along an arc relative to the device.

Abstract: A submarine vehicle may include a storage area for storing loads. The submarine vehicle may further include a pressure hull. The submarine vehicle is configured to pick loads up from a seabed and/or set loads down on the seabed. The storage area may be positioned outside the pressure hull and, in some examples, between numerous pressure hulls. Further, the storage area may include a lower hatch disposed on an underside of the pressure hull or an upper hatch disposed on a top side of the pressure hull. Some submarine vehicles may include a load transporting system for picking the load up from the seabed, setting the load down on the seabed, and/or conveying the load within the storage area.

Abstract: An autonomous underwater system for environmental monitoring including a multidisciplinary underwater station including onboard instrumentation, at least one autonomous modular underwater vehicle movable inside an area to be monitored along an assigned route, and at least one external instrumental modulus which can he connected the vehicle, wherein the multidisciplinary underwater station includes a docking area, an interface system, an equipping system for supplying the vehicle with instrumental moduli, and a management system.

Abstract: Apparatus suitable for use in positioning ceiling or wall panels in predetermined locations. The apparatus includes one or more channel means shaped to receive at least part of a panel in use, said channel means at least partially defined by one or more substantially planar outer walls and at least one inner wall. At least part of the inner wall depends away from the outer wall thereby forming the opening into said channel means through which the ceiling or wall panel is inserted in use.

Abstract: The invention relates to a steering control device for boats that includes a drive shaft, the rotation of which in one direction or in the opposite direction, by way of a control member, such as a steering wheel or helm mounted or mountable thereon, causes a steering input for an outboard motor or rudder. The steering input is generated by a transmission member, housed into a case, configured to transmit the rotational motion of the shaft to an actuator, associated or associable to the motor or rudder, through a transmission circuit. The device includes a first stationary part configured to be fastened on the bridge of the boat and a second movable part integral with the case of the transmission member.

Abstract: The object of the invention is a method and an apparatus in an electric propulsion arrangement of a sailing vessel, wherein the sailing vessel has a traction device provided with an electric motor and with a propeller mechanism, the electric motor of traction device is arranged to be used, if necessary, in forward drive and reverse drive as well as during sailing as a generator for charging the accumulators of the sailing vessel. The propeller mechanism comprises a propeller hub with blades, a hollow propeller shaft fixed at its first end to the propeller hub, a shaft controlling the pitch angles of the propeller blades, said control shaft rotating inside the propeller shaft, and a servomotor rotating the control shaft. The servomotor is fixed to the second end of the propeller shaft to be rotatable along with the propeller shaft.

Abstract: A ventilation valve (100) for ventilation of a tank (not shown) containing a liquid where the liquid surface fluctuates over time at the same time as the ventilation valve (100) obstructs external liquid to enter into the tank through the ventilation valve, is described. The ventilation valve (100) comprises a structural main housing (1, 2) containing a valve unit (3, 4, 5) and respective ventilation channels (6, 7, 9, 10, 13, 14, 16) providing open communication between the tank and the atmosphere, and the valve unit includes a movable float body (4) obstructing liquid ingress into the tank through said ventilation valve (100). The valve unit is in the form of a replaceable valve module which includes the float body (4) which is received in a valve housing (3). The structural main housing (1, 2) includes a socket part (2) and one from the socket part (2) releasable cover part (1) in order to provide access to the replaceable valve module (3, 4, 5).

Abstract: A ballast water treatment device includes a filtration device and an irradiation device that irradiates, with ultraviolet rays, filtered water that has been filtered. The filtration device is a device that removes 99.999% or more of L-size organisms having a minimum part size of 50 ?m or more, and 90% or more of S-size organisms having a minimum part size of 10 ?m or more and less than 50 ?m. The irradiation device is capable of sterilizing the filtered water at a flow rate of 250 m3/h and a power consumption of 13 kW to eliminate 90% of S-size organisms immediately after a sterilization treatment.

Abstract: An aviation laminate includes an intumescent backer sheet covered by a decorative sheet. The aviation laminate is generally fire-resistant, may be structural, and may be used to construct various components within an aircraft cabin that may be held to government/regulatory fire mitigation requirements.

Abstract: In one embodiment, an apparatus comprises a thermal barrier configured to surround at least a portion of a driveshaft and to protect the driveshaft from heat. The thermal barrier comprises an inner wall forming a cavity in which the driveshaft lies, an outer wall enclosing the inner wall, and a space between the inner wall and the outer wall. The space is evacuated and forms a vacuum.

Abstract: A thermal insulation system for an aircraft is provided. The thermal insulation system includes a carrier and a container. The carrier has an interior surface including a first plurality of magnets that generate a first magnetic field, and an exterior surface that is thermally coupled to at least one high temperature component. The container is surrounded by the interior surface of the carrier, has an exterior surface including a second plurality of magnets that generate a second magnetic field oriented opposite the first magnetic field, and has an interior surface that is thermally coupled to at least one temperature sensitive component. The first magnetic field and the second magnetic field generate a gap between the carrier and the container to reduce a heat transfer from the at least one high temperature component to the at least one temperature sensitive component during operation of the aircraft.

Abstract: A propulsion system comprises a propeller and a driving device coupled with the propeller. The propeller comprises a hub having a receiving hole, a plurality of blades connected to the hub, and a connecting surface. The driving device comprises a body portion, an elastic abutting member disposed on the body portion and configured to abut against the connecting surface, and a lock portion disposed on the body portion and including a first snap-fitting portion. A second snap-fitting portion is arranged on an inner wall of the receiving hole and is configured to snap with the first snap-fitting portion.

Abstract: A pilot control interface and method are described for selective control of an autopilot system by a pilot of an aircraft in which the autopilot system is installed. The pilot control interface includes a passive network that is selectively switchable between a plurality of states across an output interface that is made up of no more than two conductors that are in electrical communication with the autopilot system. Modification of a current autopilot flight mode can be performed incrementally or continuously based on respective momentary and continuous pilot input actuations.

Abstract: A method is provided for improving aircraft engine operating efficiency during flight in aircraft driven on the ground by electric taxi systems that extends engine warm up and cool down time during ground operations without increasing the time an aircraft spends on the ground. Aircraft are driven by electric taxi systems between landing and take off with the main engines simultaneously maintained at throttle setting for time periods that ensure even and symmetrical heating or cooling for all engine components. When the aircraft reaches a location where idle or take off thrust is required before take off, engine thrust may be increased without the adverse effects of differential thermal expansion of engine components during flight. Aircraft engines may be designed to rely on electric taxi operation and extended warm up and cool down times without delaying push back or taxi-in or otherwise negatively impacting airport operations.

Abstract: An aerodynamic lift enhancing system for increasing aerodynamic lift generated by a body of an automotive flying vehicle is disclosed. The automotive flying vehicle includes a vehicle body enclosing a passenger compartment and having an upper surface at least partially defined by a hood, a roof extending over the passenger compartment, and a front windshield disposed between the hood and roof. The front windshield includes a leading edge positioned proximate a trailing edge of the hood and a trailing edge positioned adjacent the roof. The automotive flying vehicle includes wings extending laterally outward from the vehicle body. The aerodynamic lift enhancing system includes an air discharge nozzle located upstream from the leading edge of the front windshield, the air discharge nozzle operable to discharge a stream of air over the upper surface of the vehicle.

Abstract: A system and method for controlling hypersonic boundary layer transition for a hypersonic flight vehicle are disclosed. The reduction or elimination of hot streaks that naturally occurs in the boundary layer transition process during hypersonic flight is achieved by utilizing various techniques. One such technique utilizes roughness elements to counteract streak development. The techniques for reducing or eliminating the streaks are tailored such that the nonlinear stages of transition are profoundly altered. This results in significant drag reduction, and consequently an increase in range of the vehicle, and also a reduction of the weight penalty due to the Thermal Protection Systems (TPS) as less protective material would be required, thus allowing for an increased payload and/or range of the vehicle.

Abstract: The VTOL aircraft of the present invention has fixed-wings which can be monoplane, biplane or tri-plane and tiltable rotors on outriggers which extend from the fuselage and/or wings. The rotors on the outriggers can be driven by engines located in the fuselage or wings via a transmission system such as a shaft, pulley, or pressurized air using pumps. If rotors are driven by jets at the tips, fuel is fed through pipes inside of the outriggers. The rotors and engines can be located at the ends of the outriggers or the rotors may be separate from the engines and tilting only the rotors reduces structural requirements and weight of the aircraft. The rotors can be tilted over ninety degrees from the vertical position forwards and backwards, sideways if needed for lateral movement. The outriggers can be configured in various ways depending upon how many rotors are used and where the engines are located.

Abstract: A propulsion system is provided, including a first propulsion unit, a second propulsion unit, a rotor, a first coupling and a second coupling. The first propulsion unit is configured for being fixedly mounted to an airframe. The rotor is configured for being pivotably mounted with respect to the first propulsion unit to allow selectively pivoting of the rotor from a horizontal mode to a vertical mode. The first coupling is configured for selectively coupling and decoupling the rotor with respect to the first propulsion unit. The second coupling is configured for selectively coupling and decoupling the rotor with respect to the second propulsion unit, independently of the first coupling.

Abstract: A vehicle, includes a main body. A fluid generator is coupled to the main body and produces a fluid stream. At least one fore conduit and at least one tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the fore conduit, coupled to the main body and respectively coupled to a starboard side and port side of the vehicle. The fore ejectors respectively comprise an outlet structure out of which fluid flows. At least one tail ejector is fluidly coupled to the tail conduit. The tail ejector comprises an outlet structure out of which fluid flows. A primary airfoil element is coupled to the tail portion. A surface of the primary airfoil element is located directly downstream of the first and second fore ejectors such that the fluid from the first and second fore ejectors flows over the such surface.

Abstract: A disposable unmanned aerial glider (UAG) with pre-determined UAG flight capabilities. The UAG comprises a flight module comprising at least one aerodynamic arrangement; and a fuselage module comprising a container configured for storing therein a payload and having structural integrity. The container is pressurized so as to maintain structural integrity thereof at least during flight, so that the UAG flight capabilities are provided only when the container is pressurized.

Abstract: A tethered unmanned aerial system (UAS) is described, wherein the flight of one or more UASs may be used in connection with a water and light display.

Abstract: A method for collecting acoustic data from an industrial machine is disclosed. The method may include: providing an unmanned aerial vehicle (UAV) having an acoustic receiver attached thereto; and positioning the unmanned aerial vehicle at a specific location so that the acoustic receiver collects acoustic data from the industrial machine at the specific location. An acoustic receiver is attached to the UAV for collecting acoustic data from the industrial machine. An acoustic filter is attached to the acoustic receiver and the UAV for filtering unwanted sound from the acoustic data. Acoustic data can be used by a flight control system to identify a specific location relative to the industrial machine that is a source a specific acoustic signature emanating from the industrial machine.

Abstract: An unmanned aerial system (UAS) that displays an image, video or other effect is described. The UAS may include a camera that captures the image for display. The UAS may be used in connection with a water display, and multiple UASs may operate together.

Abstract: The present invention relates to systems for protecting against sun's damaging rays, and against unwanted onlookers like drones. The systems comprise a drone and a covering member attached to the drone. In one aspect, a Flight Control System, FCS, flies the drone in a selected spot. In one embodiment, the covering member acts like an overhead covering, and a measuring device provides the FCS information for flying the drone on a holding position over a stationary user. In another embodiment, a measuring device enables the FCS to fly the drone over a non-stationary user and to tracking him. Further, the FCS adjusts the drone position with respect to the position of either the sun or a detected drone in the sky. In another embodiment, a radio control, transmitter receiver, pair is used to communicate user's requests to the FCS. One request may be to turn on the motors.

Abstract: Systems and methods are provided for decoupling movable control surfaces. Such systems may detect that a movable control surface is in a non-responsive state, such as a hard-over, and decouple the movable control surface from the main, fixed, control surface. The control surfaces may be coupled to an aircraft. A controller of the aircraft may detect the nonresponsive movable control surface, provide instructions to decouple the movable control surface, and compensate for the decoupling of the movable control surface in instructions provided to flight systems of the aircraft.

Abstract: An aft pivot assembly can include a mount device securable to an aft portion of a payload of an aircraft for facilitating release of the payload. The aft pivot assembly can include a shaft operable with the mount device and a release component, the shaft being rotatable about multiple shaft axes relative to the mount device so as to either minimize or eliminate carriage loads about the aft portion, while reacting jettison loads during a jettison event or phase. The rotation of the shaft about its shaft axes can further be limited via a limit device. As the payload transitions from a carriage phase to a jettison phase, the shaft moves in multiple degrees of freedom and in multiple axes relative to the mount device.

Abstract: In an illustrative embodiment, a premium class seating arrangement for an aircraft cabin includes at least three passenger suites, each passenger suite including a seat movable between an upright position and a horizontal bed position and an ottoman which expands a surface area of the bed position. The passenger suites may cooperatively form a nested arrangement capable of nesting with identical passenger suite arrangements longitudinally within the cabin area. At least two of the ottomans of the passenger suites may be longitudinally offset in installation position. Each passenger suite in the arrangement is afforded direct aisle access without interference by another passenger suite.

Abstract: A hybrid tube, in particular for an aircraft seat structure includes ribs intended to receive the hybrid tube. The hybrid tube includes a monolithic carbon tube and at least one sleeve made from a ductile material and connected to the carbon tube by means of gluing, shrink-fitting or over-moulding.

Abstract: An airplane seat device includes at least one airplane seat, and with at least one console arranged, viewed in a flight direction, in front of the airplane seat, and with at least one airbag element which is configured to protect in a crash event a passenger sitting in the airplane seat from crashing onto the console. At least one airbag element features, in a fully deployed state, at least in a head-impact zone, a thickness which is smaller than a thickness in at least one shoulder-impact zone.

Abstract: An aircraft includes a wing having a first upstream longeron and a second downstream longeron extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream longeron via at least one first and second fastener.

Abstract: To surely grasp an unlocked state of a cowl member while suppressing cost and time necessary for measures against forgetting of locking of an engine nacelle. An aircraft according to the present invention includes: an engine (3) that includes an engine main body (4, 5) outputting thrust force and an engine nacelle (7) surrounding the engine main body (4, 5); an engine pylon (2) that supports the engine main body (4, 5) to a main wing (1) and axially supports a cowl member (8) to be openable, the cowl member (8) configuring the engine nacelle (7); a locking part (30) that locks the cowl member (8) of the engine nacelle (7) in a closed state; and one or more light emitting sections (15) that are disposed inside the cowl member (8) and show an unlocked state of the cowl member (8).

Abstract: In order to reduce the size of the attachment arrangement between an aircraft engine and its attachment device, an engine assembly is provided for which the primary structure of the attachment device includes a central box and two movable structural cowls. Further the arrangement for attaching the engine on the structure comprises a group of main ties laid out in a main transverse plane for absorbing forces crossing a front end of the movable structural cowls, this group comprising three main shearing pins radially oriented and distributed around a longitudinal axis of the engine, each pin crossing a first shearing orifice provided on a fitting secured to the hub of the intermediate case on the one hand, and a second shearing orifice provided on one of the movable cowls or on its connecting structure to the central box on the other hand.

Abstract: A rotorcraft including a fuselage, one or more motor-driven rotors for vertical flight, and a control system. The motors drive the one or more rotors in either of two directions of rotation to provide for flight in either an upright or an inverted orientation. An orientation sensor is used to control the primary direction of thrust, and operational instructions and gathered information are automatically adapted based on the orientation of the fuselage with respect to gravity. The rotors are configured with blades that invert to conform to the direction of rotation.

Abstract: A method and a device for controlling a coupling mechanism arranged between an engine and a main mechanical power transmission gearbox MGB of a rotary wing aircraft. First determination means enable a first measurement to be taken giving the speed of rotation of said engine, which speed, on being compared with a setpoint speed for said engine, makes it possible to determine a “ready to engage” state for said coupling mechanism. Third determination means serve to determine a maximum torque that can be accepted by said MGB. While engaging the coupling mechanism, a control system for controlling said engine regulates said speed of rotation of said engine on said setpoint speed, while ensuring that the torque delivered by said engine is less than or equal to said maximum acceptable torque.

Abstract: A fuel cell power pack used as a power source in a multicopter includes a fuel tank and a fuel cell stack for producing electrical energy using hydrogen supplied from the fuel tank and supplying the electrical energy to a battery, and since the fuel cell stack is disposed at a certain point of an arm extended from the aircraft body in the radius direction (a point affected by a descending air current generated by each rotating blade), the electrical energy can be produced using the descending air current generated by the rotating blade without configuring a separate blowing apparatus.

Abstract: An aircraft is provided and includes an airframe defining a cockpit with first and second control stations configured for co-activation and complementary deactivation, flight control assemblies disposed at multiple locations of the airframe and a flight control computer (FCC). The FCC is configured to control operations of the flight control assemblies in accordance with current flight conditions and commands received at activated ones of the first and second control stations that are inputted by a flight crew. The FCC includes a secondary monitoring system to identify when commands are input at a deactivated one of the first and second control stations, to determine whether the commands are indicative of normal and intentional piloting inputs and to generate control station cues in an event the commands are indicative of normal and intentional piloting inputs to alert the flight crew of a hazardous condition or automatically turn the station back on.

Abstract: A helicopter-hoist system is described. The system may include: hoist equipment, illumination systems, range-measuring equipment, camera(s), communication systems, display devices, processing/control systems including image-processing systems, and power-management systems. The system may also include a smart-hook for measuring a load on the hook. Based on the measured load on the cable, the lighting may be illuminated in different manners. In another aspect, the system may communicate with display devices, which render images of a mission to helicopter crew members or other observers.

Abstract: A three-dimensional infrared laser aircraft landing-guiding system with high directivity is described. The system utilizes a highly penetrable and highly directional infrared laser source to generate an optical image via an optical image generating apparatus. The generated optical image involves the information for aircraft landing, and the information covers a large range of flying areas to make the optical image detectable for an aircraft. With the information provided by the optical image, the aircraft can be guided to the best landing path. The infrared laser source is highly directional and can emit a laser light to specific directions, reducing waste of energy, increasing navigation distances, and improving anti-jamming capability.

Abstract: A real-time galley power management and fault monitoring system for an aircraft manages a status of power consumption of a plurality of galley inserts inside a galley complex of an aircraft and monitors fault status of each galley insert of the plurality of galley inserts.

Abstract: A water and lighting display that includes an unmanned aerial system (UAS) is disclosed. The UASs may illuminate water shot out of the water fountains, may fly in formation or may include removable payloads.

Abstract: A height adjustment device for a rotunda can comprise: an outer column which fixes a rotunda and ascends and descends; an inner column which is connected to the outer column; a vertical screw which is placed on the lower end of the rotunda; a nut which is interlocked in correspondence to the outside diameter of the vertical screw; and rails which are provided on one side of the outer column or the inner column and are formed in correspondence to each other so as to assist the ascent and descent of the outer column.

Abstract: A method of installing a fixture, such as a bracket, in a fuselage structure of an aircraft or spacecraft, includes providing or generating a three-dimensional digital model of the fixture; arranging a head of an additive manufacturing apparatus in, on or adjacent the fuselage structure; and forming the fixture in situ in or on the fuselage structure with the head of the additive manufacturing apparatus based upon the digital model of the fixture. The fixture is installed in or on the fuselage structure by bonding or fusing the fixture to the fuselage structure as the fixture is formed, and the step of forming the fixture in situ includes: forming an anchored portion of the fixture which is non-movably fixed to the structure; and forming an operable portion of the fixture which is movable relative to the anchored portion.

Abstract: A process for assembling aircraft control surfaces (1, 1?), in particular high-lift devices and wing portions, allows implementing smooth control surfaces in short times, wherein the control surface is defined by an upper skin (2) and by a lower skin (9), the upper skin being destined to form the leading edge (4) of the control surface by means of the connection to a front spar (3), wherein the upper skin and the lower skin are made of a laminar composite material which, not yet hardened, is fastened to structural elements (3, 5, 6, 7) of the control surface by means of an adhesive; and wherein the resin of the composite material and the adhesive are hardened simultaneously in autoclave.

Abstract: A method of repairing an acoustic core cell of an acoustic sandwich panel is provided. The method comprises inserting a core repair splice adjacent to a number of damaged walls of the acoustic core cell of the acoustic sandwich panel, nesting the core repair splice onto the number of damaged walls, and bonding the core repair splice to the number of damaged walls and thereby to repair the acoustic core cell of the acoustic sandwich panel.

Abstract: This invention is pioneering a Strategic Trans-orbital Carrier (herein called a carrier’) which merges the technologies attributes of a plurality commercial jet engines with a plurality reusable rocket engines to provide capabilities permitting a smooth computer-controlled transition from terrestrial air space to insertion into and thru low earth orbit (LEO) and into high geostationary earth orbit (GEO). A carrier would return back to terrestrial air space with carrying approximately 60 tons of any type of customers' defined cargo and passengers which would include intermodal container modules, complete DoD military strategic devices; heavy industrial outfitting apparatuses; building components for infrastructure complexes; personnel and robots; and space defensive materials to an in-situ space complex.

Abstract: A habitation module that provides an artificial gravity environment. In one embodiment, the habitation module includes a core structure having cylindrical sections spaced apart from one another, and a hub that slides over one of the cylindrical sections of the core structure to span a distance between the cylindrical sections. The hub includes a plurality of portals spaced radially around a circumference of the hub, and gravity chambers attach to portals of the hub. A drive mechanism rotates the hub about an axis in relation to the core structure to simulate a gravitational force within the gravity chambers. Rotary seals form an air-tight seal between the hub and the cylindrical sections of the core structure so that the interior of the hub and the gravity chambers may be pressurized.

Abstract: A habitation module that provides an artificial gravity environment. In one embodiment, the habitation module includes a stationary structure and a rotating structure. The stationary structure includes circular side walls that are coaxially aligned and attached by one or more support beams. The rotating structure slides onto the stationary structure, and rotates about an axis in relation to the stationary structure. The rotating structure includes a cylindrical hub, and a plurality of gravity chambers that are permanently affixed to the cylindrical hub and project radially from the axis. Radial seals form an air-tight seal between the rotating structure and the stationary structure.

Abstract: The present invention relates to a filling container including a joint, where a side of the joint is provided with an inlet, another side of the joint is provided with a tube insertion cavity, and an inner end of the tube insertion cavity is connected to the inlet; a hollow tube bundle, including several hollow tubes, where an upper part of the hollow tube bundle is entirely inserted into the tube insertion cavity; a container, mounted at a lower end portion of a hollow tube by using an elastic fastener, where an inner cavity of the container is in communication with an inner passage of the hollow tube; and a holding mechanism, mounted on the joint at the tube insertion cavity, where the holding mechanism enables the tube insertion cavity to contract and hold the hollow tube bundle.