Abstract: A wind-propelled vessel is described herein. The vessel includes at least one hull and at least one set of paired masts. Each paired mast of the at least one set of paired masts has a first mast located to one side of the vessel and a second mast located on the opposite side of the vessel. Also, each mast of the at least one set of paired masts has a spar located at or near the top of the mast. Moreover, each one of the spar located at or near the top of the mast extends inwards towards a center plane of the vessel, and an inward end of the spar is connected by a connector to another inward end of another one of the each one of the spar located at or near the top of the mast.

Abstract: In order to provide a rigid sail or aerofoil sail which has a lower overall weight, is cost-effective to manufacture and does not affect the passing under bridges, power lines or similar structures arranged over busy waters, in the case of a rigid sail for vessels, in particular, for large ships, such as bulk carriers, tankers, car transporters or bulkers, comprising a mast and a first aerofoil wing body mounted on the mast with a base and a head, wherein the mast is inserted through the base into the first aerofoil wing body and is arranged within the first aerofoil wing body, it is proposed that the mast, starting from the base, does not extend beyond a maximum height of the first aerofoil wing body, in particular, less than 75% of the maximum height.

Abstract: An autonomous sailing vessel may include a hull, a mast, a sail, and a sail release device. The mast may be mechanically coupled to the hull. The sail may be mechanically coupled to the mast. The sail release device may be operably coupled to the sail and may be configured to automatically release the sail to spill excess wind. Alternatively or additionally, the sail may include a fore sail element coupled to the mast and an aft sail element rotatably coupled at a fore of the aft sail element to an aft of the fore sail element. In this and other embodiments, the autonomous sailing vessel may further include a camber control assembly to automatically set a camber angle between the fore and aft sail elements.

Abstract: Embodiments described herein relate generally to a sailing vessel that can substantially obviate the heeling problem experienced by classical sailboats. During navigation, the sailing vessel is driven forward by an aerodynamic force exerted by wind on the sail, and balanced by a hydrodynamic force exerted by water on a float on the stern of the sailing vessel, the aerodynamic force and the hydrodynamic force being parallel or substantially parallel to a longitudinal axis of the sailing vessel.

Abstract: Disclosed herein are various devices for the support of an outboard motor. The device having a body with a plurality of notches shaped to couple various pieces of the boat, outboard motor, and/or mounting bracket.

Abstract: A device to support an outboard motor in a raised position, the device including an elongated support body having first and second ends, a coupling member provided at the first end of the support body and configured to be removably coupled to a stern bracket, and a pair of stabilizing members coupled proximate the second end of the support body, wherein the second end of the support body is configured to contact a motor bracket to maintain the outboard motor in the raised position, and wherein the pair of stabilizing members are configured to be fixable in a position to contact opposite sides of the outboard motor to stabilize the outboard and inhibit lateral movement.

Abstract: An aerial vehicle (1) in which forward motion is developed by changing the position of the buoyancy centre and the position of the centre of gravity of the aerial vehicle (1). The aerial vehicle (1) has an envelope (12) which is a body of revolution about a central axis (X-X). The envelope (12) comprises a film and contains a lighter than air gas and wings (13, 14) one each extending laterally either side of the envelope (12).

Abstract: The present invention is realized by apparatus and methods for harvesting, storing, and generating energy by permanently placing a large rigid buoyant platform high in the earth's atmosphere, above clouds, moisture, dust, and wind. Long, strong and light tethers can connect the buoyant structure to the ground which can hold it in position against wind forces. Weights suspended from the buoyant platform with cables are raised and lowered by electric winches to store and release gravitational potential energy. High voltage transmission lines electrically connect the platform to the earth's surface. Electrical energy from the high voltage transmission lines or from photovoltaic arrays on the platform can be stored as gravitational potential energy and subsequently released as electricity from generators driven from the stored gravitational potential energy and used on the platform or transmitted via the high voltage transmission lines.

Abstract: A moisture control system includes an anode coupled to an insulation blanket that is positioned between an inner wall and an outer wall of an aircraft fuselage, a cathode coupled to an interior surface of the outer wall, and a power control unit coupled to the anode and the cathode to apply voltage across the anode and the cathode. When the voltage is applied across the anode and the cathode, moisture is drawn away from the anode and toward the cathode on the interior surface of the outer wall and guided along a drainage path provided via structural members disposed between the inner wall and the outer wall toward a drainage port.

Abstract: In a propulsion unit for an aircraft, including a nacelle and a turbojet engine supported by a pylon, a nacelle includes an outer shroud, a fixed internal structure defining, with the outer shroud, an annular space in which a cold air stream can circulate, and a sealing ring positioned between the fixed internal structure and the pylon. The sealing ring is used to separate a cold pylon zone from a hot engine zone. The propulsion unit includes a ventilation device allowing a portion of cold air of the cold air stream to be deviated to the sealing ring in order to ventilate the sealing ring.

Abstract: An aerodynamic brake includes a rigid panel having a panel leading edge portion and a panel trailing edge portion. The panel trailing edge portion is pivotably coupled to a vehicle body. The aerodynamic brake also includes a flexible sheet having a sheet lower edge portion coupled to the vehicle body, and a sheet upper edge portion coupled to the panel leading edge portion. The aerodynamic brake further includes a panel actuator configured to pivot the rigid panel between a stowed position and a deployed position. In the stowed position, the rigid panel is located proximate the vehicle body and covers the flexible sheet in a folded state. In the deployed position, the panel leading edge portion is pivoted away from the vehicle body and the flexible sheet is in an open state exposable to an oncoming airflow for generating aerodynamic drag for slowing the vehicle.

Abstract: A propulsion assembly for an unmanned aerial vehicle (UAV) includes a motor configured to rotate in a first direction, a propeller seat configured to be driven by the motor to rotate in the first direction and to receive a propeller, and a sensor configured to collect sensing data useful for determining whether the propeller is locked to the propeller seat, without requiring operation of the motor.

Abstract: Methods and systems for governing an aircraft propeller of an engine are described. The method comprises obtaining a fluid flow command for speed control of the propeller, determining pulse parameters of a pulse width modulated valve control signal for actuating a two-position solenoid valve in accordance with the fluid flow command based on an average fluid flow through the solenoid valve and an opening and closing time of the solenoid valve, generating the valve control signal with the pulse parameters as determined, and transmitting the valve control signal to the solenoid valve for actuating the solenoid valve, thereby controlling the speed of the propeller.

Abstract: According to a first aspect of the invention, there is provided a method for operating a multicopter experiencing a failure during flight, the multicopter comprising a body, and at least four effectors attached to the body, each operable to produce both a torque and a thrust force which can cause the multicopter to fly when not experiencing said failure.

Abstract: Aircraft fly-by-wire systems and related vehicle electrical systems are provided. In one embodiment, an electrical system suitable for use with a control surface of a vehicle, such as an aircraft, is provided. The electrical system includes an asynchronous intermodule bus arrangement, a first vehicle control module, and a second vehicle control module. Each vehicle control module includes a respective interface arrangement to obtain and exchange data from different sensing arrangements with a first frequency, and a respective processing system to obtain the sensed data and determine actuator commands based on the sensed data with a lower frequency.

Abstract: A micro detecting device includes a flying main body, at least one fluid actuation system, an image capture system and a controller. The fluid actuation system is disposed within the flying main body and includes a driving module, a flow guiding channel, a convergence chamber, plural valves and a fluid discharging zone. The driving module is consisting of plural flow guiding units for transporting fluid. The flow guiding channel includes plural diverge channels which are in fluid communication with plural connection channels. The convergence chamber is in fluid communication between the corresponding diverge channels. The valves are respectively disposed in the corresponding connection channels and controlled in open/closed state for the corresponding connection channels. The fluid discharging zone is in communication with the connection channels. The image capture system is used to capture external image. The controller is connected to the valves to control the valves in the open/closed state.

Abstract: The aerodynamic element includes an ionization system which ionizes flow of air flowing over the top face of the aerodynamic element and a control system which generates at least one electromagnetic force associated with an electrical current and a magnetic field, the at least one electromagnetic force being oriented in the direction opposite to that of the flow of the ionized air flow such that the electromagnetic force reduces the instabilities of the flow of the airflow.

Abstract: An orifice plate includes a wear-resistant inner diameter surface, an outer diameter surface, a first side surface extending between the wear-resistant inner diameter surface and the outer diameter surface, and a second side surface extending between the wear-resistant inner diameter surface and the outer diameter surface, the second side surface disposed opposite the orifice plate from the first side surface. The orifice plate may comprise a body portion comprising a first material. The wear-resistant inner diameter surface may comprise a second, wear-resistant material.

Abstract: A drone includes a fuselage and a plurality of housing structures for a plurality of engine units. The mechanical connection between each engine unit and each housing structure for the engine unit has: a ball joint arranged in the axis of rotation of the engine unit, opposite the rotor; and a flexible connecting member connecting the engine unit to the housing structure for the engine unit.

Abstract: An advancing blade concept rotorcraft includes an airframe and a pylon assembly subject to vibration. The pylon assembly includes a dual rotor system having coaxially disposed top and bottom rotor assemblies that counter rotate relative to one another. The advancing blade concept rotorcraft includes a vibration isolation system including at least one pylon link coupled to the airframe and the pylon assembly. The pylon link includes a Liquid Inertia Vibration Eliminator unit operable to reduce transmission of the pylon assembly vibration to the airframe. The advancing blade concept rotorcraft includes active force generators adjacent to the pylon assembly. The active force generators include a first active force generator producing a force in a first direction and a second active force generator producing a force in a second direction to counteract multidirectional oscillations of the pylon assembly, thereby reducing vibration of the advancing blade concept rotorcraft.

Abstract: Embodiments of the present invention enable a user of a drone to operate it more quietly. Embodiments of the present invention relate to such a system, apparatus, and a method of and for a drone that may be quiet, that can fly far while minimizing the need to recharge, that may have protective shells, that may employ operational redundancy, that may provide stealth capabilities due, for example, to the design of the shell, and that may allow a drone to stay in position at, for example, 329,999 feet for months. In one embodiment of the present invention, electro-magnetism is used to propel a drone while another embodiment uses an expandable outer shell. The embodiments, while also increasing a drone's range, provide enhanced maneuverability due to the unique shape and drive and steering systems of the drone. Embodiments may provide stealth and overall convenience, together potentially resulting in increased safety to creating a class of sub-space vehicles.

Abstract: A biplaner rotor blade has an upper airfoil section connected to a lower airfoil section such that the upper airfoil and lower airfoil are rotated in separate planes—an upper plane and a lower plane. The upper airfoil has a root end attached to a hub at an upper location of the hub and the lower airfoil has a root end attached to the hub at a lower location of the hub. The upper airfoil converges with the lower airfoil to form a blade tip end at the outermost portion of the blade, thus generating lift along two geometric planes.

Abstract: A method of controlling a tail rotor system of a helicopter includes pivoting a swashplate of the tail rotor system about an axis passing through a diameter of the swashplate. Pivoting the swashplate causes a first linkage of a first pair of linkages coupled between the swashplate and a collective crosshead to move in a first direction and a second linkage of the first pair of linkages coupled between the swashplate and the collective crosshead to move in a second direction that is opposite the first direction. The movement of the first and second linkages causes a plane of rotation of a pair of rotors of the tail rotor system to cant relative to a centerline of a mast of the tail rotor system.

Abstract: A hybrid electric jet powered aircraft including a fuselage member, a power unit, a set of wing members, and an emergency safety unit. The fuselage member includes a cabin having a plurality of enclosed seating elements for transporting a plurality of passengers and a cockpit having a plurality of seating elements for one or more operators of the aircraft. The power unit includes at least one electric powered motor and at least one jet fueled powered engine. The set of wing members for lifting the fuselage member. The set includes two pairs of wing members, wherein each pair of wing members is attached at its proximate end to the fuselage member on opposite sides of the fuselage member from one another. Each wing member has a tilting ducted fan attached to its distal end. Each ducted fan is tilted in a first position for horizontal forward flight and each ducted fan is tilted in a second position for vertical flight.

Abstract: A method, system, and non-transitory computer-readable medium is provided for enabling a distributed power transfer network for an aerial vehicle, such as a drone. The distributed power transfer network may include wireless power transfer systems that may allow wireless charging and powering of devices within a distance of 10 meters. In some example embodiments, the distributed power transfer system may include at least one transmitter generating at least one transmission signal. The distributed power transfer system may further include a plurality of transducers each conducting a respective transmission signal of the at least one transmission signal, the plurality of transducers being positioned at respective different locations for producing from the respective transmission signals magnetic fields defining associated power transfer regions for transmitting wirelessly with the associated magnetic fields, power to aerial vehicles located in the power transfer regions.

Abstract: A method for detecting a mounting error of an accelerometer includes acquiring actual output data of the accelerometer mounted to an unmanned aerial vehicle (“UAV”) while the UAV is in a hover state. The method also includes determining a mounting error angle of the accelerometer based on the actual output data.

Abstract: A drone control method is provided. The method may be responsive to drone recharge energy cost being greater than a predefined threshold and include commanding a processor of the drone to execute actions that preclude the drone from recharging. The method may also be responsive to drone charge level falling below a charge threshold selected only while the drone recharge energy cost exceeds the predefined threshold and include commanding the processor to execute actions to recharge the drone.

Abstract: A tandem wing aircraft having a fore wing, an aft wing, and a middle wing, attached relative to the aircraft and each other such that the middle wing provides a substantial portion of the total lift at landing speeds, and a minimal portion of the total lift at cruise speeds. At cruise speeds, induced drag is minimized, permitting higher speeds, greater fuel efficiency, and/or greater payload. Advantageously, the wing loading at cruise speeds is higher providing better passenger comfort while still providing controllability and safety at landing speeds.

Abstract: A device for securing at least one sling for transporting a load under a helicopter, the securing device comprising at least a first strap and at least a second strap, a connection mechanism configured, in the closed state, to connect the straps, to form a comprehensive security strap capable of supporting a sling and, in the open state, to release the straps for releasing the sling, and an actuator configured to open the connection mechanism following a mechanical effort being introduced, the connection mechanism comprising cascading reduction means configured to reduce the resistance force during the opening of the connection mechanism generated by the load connected to the sling.

Abstract: Embodiments are provided for a method and system for operating a service light integrated with a reading light. Some embodiments include providing a reading light and a service light, wherein the reading light and the service light are coupled to a switch, and receiving a first input to operate the reading light. Also, some embodiments include receiving a second input to operate the service light, wherein the first input and second input are received by the switch, and illuminating the reading light and the service light responsive to the first input and the second input, wherein the service light illuminates a switch cover operably coupled to the switch.

Abstract: A bypass flow regulator for a vacuum waste system (VWS) is disclosed. The bypass flow regulator includes a valve assembly installable in an aircraft vent line leading outside the aircraft from an onboard VWS waste tank. The vent line directs an airstream pumped from the waste tank to an external outlet under suction (from which outlet the airstream is ejected from the aircraft). The valve assembly includes a group of valves (e.g., umbrella valves) set into the path of the airstream. The valves may collectively modulate the flow rate of the airstream by adjusting their effective flow area.

Abstract: A seat for cabin crew, intended to be installed in an aircraft, includes a seat structure intended to be fixed to a fixed portion of the aircraft, a seat slide provided with two arms positioned on either side of the seat portion, and a seat portion mounted slidably relative to the seat slide between a retracted position and an extended position. One of the elements among the seat portion and the seat slide includes rollers capable of sliding along corresponding rails provided in the other one of the elements among the seat portion and the seat slide. The rails have a curved shape so that the seat portion forms, in the extended position, an angle of more than 10 degrees, preferably of around 14 degrees, relative to a floor of the aircraft.

Abstract: Arrangements for an aircraft passenger cabin including a seating area containing first and second passenger seats, a monument disposed at one end of the seating area, and at least one privacy divider deployable in a longitudinal direction of the seating area to divide at least a portion of the seating area for privacy. In some embodiments, the at least one privacy divider includes a first privacy divider adapted to deploy to divide the seating area forward of the first and second passenger seats and a second privacy divider deployable to the seating area between the first and second passenger seats.

Abstract: The invention relates mainly to an energy absorber for an aircraft seat, notably for a helicopter seat, comprising at least one energy-absorption element having: a first anchor point and a second anchor point, an energy-absorption zone extending between the first anchor point and the second anchor point, said energy-absorption zone being able to stretch as a tensile load is applied between the first anchor point and the second anchor point, characterized in that the energy-absorption zone has a meshed structure comprising a plurality of strands connected to one another by junction portions, and in that at least one junction portion provides a junction between at least three strands of said energy-absorption zone.

Abstract: In various embodiments, the present disclosure provides an energy attenuating mounting foot comprising a load beam having a longitudinal axis, a top surface, a bottom surface, an inner track interface lobe, and an outer track interface lobe, the inner track interface lobe and the outer track interface lobe extending laterally from the load beam, and a channel along the longitudinal axis having a depth extending from the load beam bottom surface toward the top surface. In various embodiments, the inner track interface lobe has a first length extending in a direction from the bottom surface towards the top surface and the outer track interface lobe has a second length extending in a direction from the bottom surface towards the top surface, the first length being less than the second length.

Abstract: An adjustable headrest assembly attachable to a seat back and including a linear slide and rotating links that allow the headrest to translate forward, laterally and/or about axes parallel to the seat back to provide head support in various positions. The headrest may further include lateral parts independently adjustable in angle relative to a center part to provide enhanced lateral head support. The adjustable headrest assembly is attachable to a front side of a seat back or to other adjustment mechanisms such as a vertical adjustment mechanism for moving the headrest assembly up or down relative to a seat back.

Abstract: An armrest for a seat may comprise paneling and an easy hook assembly. The easy hook assembly may include a flange and a keyhole protrusion. The flange and the keyhole protrusion may each extending beyond an exterior surface of the paneling. The flange and the keyhole protrusion may allow the armrest to be installed after the paneling is attached.

Abstract: A passenger service unit assembly that includes a frame that defines at least an oxygen opening and a service opening, an oxygen mask housing positioned adjacent the oxygen opening, an oxygen mask housing cover positioned to cover the oxygen opening, and a service cover positioned to cover the service opening. An oxygen mask that is movable between a stowed position and a deployed position is positioned in the oxygen mask housing. The oxygen mask housing cover maintains the oxygen mask in the stowed position. The oxygen mask housing cover is movable between a closed position and an open position. When the oxygen mask housing cover is moved to the deployed position, the oxygen mask drops to the deployed position via gravity. The service cover is movable between a closed position and an open position and includes at least a first passenger service unit component associated therewith.

Abstract: A method and device for reducing ice and frost on a surface comprising a wettable pattern on a surface. The pattern is wetted with water which is frozen into ice to create overlapping hygroscopic that cover the surface.

Abstract: A suspension line assembly for a parachute may comprise a plurality of suspension lines bound together at a confluence, and a dampening riser coupled to the confluence, wherein the dampening riser comprises a first length in the stowed position and the dampening riser is configured to extend to a second length in a deployed position in response to a tensile force applied to the dampening riser.

Abstract: An evacuation slide may comprise a sliding surface extending from a head end of the evacuation slide to a toe end of the evacuation slide and a truss-shaped side rail located adjacent the sliding surface. An evacuation system may comprise the evacuation slide and a charge cylinder fluidly coupled to the truss-shaped side rail.

Abstract: An assembly comprising a wing with lower spars, a mounting pylon having an upper spar and two lateral panels, a front fixing system and a rear fixing system, each comprising a beam pierced with a principal bore and, for each beam, an upper bore traversing the upper spar and a shear pin positioned in the upper bore and in the principal bore. The assembly also comprises, for each fixing system, bolts, the nut of which is accommodated in a secondary hole of the beam and the screw of which traverses the upper spar and the beam in order to be screwed into the nut.

Abstract: A system comprising a trolley which comprises a platform and wheels attached beneath the platform, an air intake of an aircraft engine, where the air intake rests on the platform so as to have its narrowest part at the top and its widest part at the bottom, and an inflatable protection item in the form of a closed envelope which is placed around the widest part of the air intake. A system of this kind makes it possible to protect the air intake from collisions that it might experience during movement of the trolley, and to increase safety by avoiding collisions between operators and the air intake.

Abstract: In the method for propelling an aircraft, to obtain electric energy, a fuel is combusted, and an electric machine is used, wherein the fuel is used to cool at least one part of the electric machine and contains natural gas. The propulsion system is configured to propel an aircraft, in particular according to the above-mentioned method. The propulsion system has an electric machine configured to obtain electric energy by combusting a fuel. The propulsion system further includes a natural gas tank configured to supply the fuel formed with natural gas, and a cooling device configured to cool at least one part of the electric machine. The aircraft has such a propulsion system.

Abstract: A vertical take-off and landing aerial vehicle (VTOL) includes a plurality of rotors for producing lift. For each respective rotor the VTOL has an auxiliary power source (APS) and a transformation gear set (TGS) both being associated with the respective rotor, and the VTOL further includes at least one main power source (MPS). Each TGS is configured to form an outgoing power towards its respective rotor from input powers received into the TGS from the MPS and from the APS associated with the respective rotor.

Abstract: This method for determining at least one fuel cosumption domain for an aircraft is implemented by an electronic device. It comprises acquiring a flight envelope as a function of the altitude and a propulsion variable. It comprises, for at least one flight phase, calculating a consumption limit curve as a function of the altitude and the propulsion variable, corresponding to a forecasted average consumption for said flight phase; and determining—from the flight envelope and the limit curve—the consumption domain as a function of the altitude and the propulsion variable and including a first consumption subdomain lower than the forecasted consumption for said flight phase and a second consumption subdomain greater than said forecasted consumption, the first and second subdomains being separated by the limit curve.

Abstract: A method of and a system for operating a fuel pump management system of an aircraft. The method comprises receiving, from a fuel gauge, an electronic reading of a level of fuel fluid contained in a fuel tank; and analysing the electronic reading of the level of the fuel fluid, the analysing comprising upon determining that the level of fuel fluid is equal or below a predetermined fuel level threshold, causing a fuel pump in communication with the fuel tank to be shut down.

Abstract: A fuel system for a rotorcraft is provided. The fuel system comprises a housing, a fuel bladder located within the housing, a first fuel reservoir, and a number of pressure relief valves. The first fuel reservoir is in fluid communication with the fuel bladder and stowed within the housing. The number of pressure relief valves are configured to divert fuel from the fuel bladder into the first fuel reservoir at a predetermined pressure such that the first fuel reservoir expands to reduce forces on the housing during a crash event.

Abstract: A method of and a system for detecting a fuel leak in an aircraft, the aircraft comprising a first engine and a second engine. The method comprises upon determining that the aircraft has reached a first mode of operation: acquiring a first baseline fuel flow of the first engine; acquiring a second baseline fuel flow of the second engine. The method further comprises monitoring a first current fuel flow measured at the first engine and a second current fuel flow measured at the second engine; and triggering a fuel leak detection based on an analysis of the first baseline fuel flow, the first current fuel flow, the second baseline fuel flow and the second current fuel flow.

Abstract: Systems and methods are disclosed for providing flexible, scalable, and controllable electrical power to an aircraft. In some embodiments, a modular power unit comprises a container containing a power generation unit, a control system, a conditioning system, and an environmental control system. The power generation unit produces a generated power. The control system provides control signals to the power generation unit and controls at least one parameter of the generated power. The conditioning system receives and conditions the generated power and provides an output power to the power bus of the aircraft. The environmental control system provides a temperature regulating fluid to the power generation unit.