Abstract: The present invention provides a vessel (10) comprising: a bow (100) having a port side and a starboard side, a pair of extended arms (101, 102) comprising: a port side extended arm (101) operationally coupled to the port side of the bow (100), and a starboard side extended arm (102) operationally coupled to the starboard side of the bow (100), the pair of extended arms (101, 102) configuring a trapezoidal zone and bifurcating an incoming wave towards the vessel (10) into three directions: towards port side, toward starboard side and a center wave into the trapezoid pool (103), thereby reducing impact of wave resistance on the vessel (10). The trapezoid pool (103) facilities the generation of air bubbles (500) by collisions of the center wave with the bow (100) and the pair of extended arms (101, 102).

Abstract: A suction anchor and method of installing the suction anchor. The suction anchor including a suction chamber bounded by: a circumferential outer wall; an upper wall; and an internal housing wall. The internal housing defining a passage for receiving wellhead components that may be secured to the suction anchor. The suction chamber has a minor upper portion and a major lower portion. The minor upper portion having internal reinforcing members extending along the inside of the upper wall from the outer walls to the internal housing. The major portion is adapted to be embedded in a seabed and the minor portion is adapted to project from the seabed when the anchor is installed. The reinforcing members serve to reinforce the upper wall of the chamber against collapse and to rigidly support the internal housing to resist forces arising from bending moments applied to wellhead components received and secured therein.

Abstract: Disclosed embodiments pertain to a paddleboard connector. A plate can be affixed to paddleboards with an integrated receiving element. A board connector member can be removably attached to each plate through the integrated receiving element. The board connector member can include an aperture and a locking mechanism for engaging with a boom. The board connector member can include a locking mechanism that can be released to allow the board connector to receive an end of the boom through the aperture. After the first end of the boom is positioned within the aperture, the locking mechanism can be engaged to hold the boom in place. A second end of the boom can be inserted into an aperture of a second board connected and held in place by engaging the locking mechanism.

Abstract: An apparatus for automated rope management on a vessel is described. The apparatus may include a first retraction unit configured to provide rotation about a first rotational axis, a second retraction unit connected to the first retraction unit and configured to provide rotation about a second rotational axis, and a base plate coupled to the first retraction unit and configured for mounting the apparatus to the vessel.

Abstract: A tab body to create shaped waves in a water behind a watercraft for water sports, such as wake surfing. Wherein, the tab body comprise a portion of a wave forming tab assembly. The wave forming tab assembly are attached to the watercraft. The tab body includes a length, a width, a height, a top surface, a bottom surface, a leading end, a trailing end, one or more hydro channels, an interior edge, an exterior edge, a planar portion and an outward angle. The interior edge is proximate to a center line of the watercraft. The exterior edge is distal from the center line of the watercraft. The planar portion located proximate to the exterior edge.

Abstract: A multipurpose portable or transportable selective fish capture system and no touch transport system is described that comprises an interconverting pontoon platform which can be adapted to include a solar and/or hydro electrical energy collection, conversion, storage and distribution system and to convert between a selective fish capture system and no touch fish transport system and an for emergency response for search and rescue or oil spill response support and oil spill collection and oil transport system.

Abstract: A buoyant trim tab comprising a shell, wherein the shell comprises a top and a bottom, and an insert, wherein the insert comprises a foam section, wherein the foam section comprises a styrene acrylo nitrile foam and further wherein the foam section comprises a low-density subsection and a high-density subsection, and wherein the buoyant trim tab is capable of floating the buoyant trim tab, an actuator, and any components used to mount the buoyant trim tab to a boat.

Abstract: The present invention provides a data communication system 1 that uses VDES, said system comprising a server 2 that transmits and receives information signals by using VHF waves, and a VDES terminal 10 that is provided on a ship and that transmits and/or receives information signals to and from the server 2, the VDES terminal 10 being provided with a communication unit 11 that transmits and/or receives information signals, a control unit 13 that analyzes the information signals to acquire information related to sea navigation and/or generates information signals including information related to sea navigation and transmits the information signals via the communication unit, and a display unit 12 having a function for displaying a display screen image for displaying information acquired by the control unit 13 and/or a function for displaying an operation screen image for inputting or forming information for the control unit to generate information signals.

Abstract: A method including by a processor and memory circuitry obtaining first position data informative of a position of first marine objects. The first position data can be obtained based on images acquired by at least one imaging device of a marine vessel, The method can include obtaining second position data informative of a position of second marine objects, wherein the second position data is obtained based on data acquired by at least one sensor of the marine vessel, At least one sensor can be different from the imaging device, wherein at least some of the first marine objects are the same as some of the second marine object. The method can include using the first position data and the second position data to estimate data informative of at least a variable height and a variable orientation of at least one imaging device of the marine vessel.

Abstract: Systems and methods for rinsing contaminants from exposed portions of a watercraft.

Abstract: A water safety garment and apparatus configured to avoid drowning can be configured to permit submergence for a predetermined period of time without inflation. After the predetermined time has passed, the garment or other apparatus can be configured to inflate to help a person wearing the garment float on top of the water to avoid drowning or other potentially harmful condition that may result from being underwater for too long. In some embodiments, a circuit may be utilized to detect the submergence condition of a person wearing the apparatus or garment. Upon a determination that the detected submergence condition has occurred continuously for a pre-determined period of time, an inflation mechanism can be actuated to force the person wearing the apparatus or garment to float to the top of the water.

Abstract: A propeller including a propeller hub, two or more blades connected with the propeller hub, and an insert having a tubular shape with an inner and outer face. The insert having a raised ridge on the inner face and the insert being inserted in at least a portion of the propeller hub.

Abstract: Paddle assembly (11) including a pair of shaft bodies (12, 14) extending between opposed ends (16, 18, 20, 22). A first end (16, 20) of each body (12, 14) is connectable to the first end (16, 20) of the other body (12, 14) to allow rotationally positioning the bodies (12, 14) relative to each other in two or more positions. A second end (18, 22) of each body carries a paddle blade (24, 25, 26, 124). The shaft bodies (12, 14) are shaped to be connectable to each other in a first configuration (28) to form a bow-shaped shaft (30), and connectable to each other in a second configuration (32) to form an S-shaped shaft (34).

Abstract: A personal watercraft includes a floatation member, a thrust assembly, a steering assembly, and a braking assembly. The assemblies may be actuated either mechanically or electrically. The thrust assembly is human powered, solar powered, or electric powered. The thrust, steering, and braking assemblies can be added after-market to an existing stand-up paddle board (SUP), or built into one or a plurality of SUPs during initial manufacturing. When the thrust assembly is human powered, it is leg or arm powered. When the thrust assembly is leg powered, the legs can move backward and forward in a sliding motion, up and down in a stomping fashion, or move in a loop trajectory. When the thrust assembly is arm powered, the arms can move forward/backward together or separately. The thrust assembly includes one or a plurality of paddles or flippers that are positioned to the side or under the SUP.

Abstract: An embodiment of an exhaust handling system for a marine vessel includes a cap connected to a top end portion of an exhaust stack of the marine vessel to form an enclosure at least partially surrounding an outlet of an exhaust pipe extending through the exhaust stack. In addition, the exhaust handling system includes a collection pipe in fluid communication with the cap such that the collection pipe is to receive exhaust from the enclosure, and a coupling connected to the collection pipe that is to connect to an exhaust cleaning assembly. The exhaust cleaning system includes a tank to receive the exhaust. The cap at least partially defines a first flow path for the exhaust that extends from the enclosure to the atmosphere. The collection pipe at least partially defines a second flow path for the exhaust that extends from the enclosure to the coupling via the collection pipe.

Abstract: A watercraft comprising a hull, a first attachment coupled to an exterior surface of the hull, a second attachment coupled to the exterior surface of the hull, and a closed-loop cooling system. The closed-loop cooling system includes a pump, a first channel at least partially formed by the first attachment, a second channel at least partially formed by the second attachment, the second channel in fluid communication with the first channel, and a coolant circulated through the first channel and the second channel by the pump.

Abstract: A system for controlling one or more propulsion devices of a marine vessel. The system includes circuitry configured to: receive a steering angle command for a propulsion device of the marine vessel; receive a trim position of the propulsion device; and generate a steering actuator position command for the propulsion device based on the steering angle command and the trim position of the propulsion device.

Abstract: A system for marine electricity generation and solid carbon production includes an offshore marine platform on which is mounted a regassification system for regassification of liquid methane; a methane splitting system producing solid carbon and gaseous hydrogen; and a power generation system producing electricity and exhaust heat. A first marine vessel is moored adjacent the marine platform for delivery of the liquid methane, and a second marine vessel is moored adjacent the marine platform for removal of the solid carbon produced by the methane splitting system. The hydrogen produced from the methane splitting system is used in a fuel stream for the power generation system. The exhaust heat from the power generation system is utilized in the methane splitting process. Also mounted on the marine platform is a solid carbon handling system disposed to manage the large amount of solid carbon resulting from the methane splitting process.

Abstract: A morphing wing (140) of the present invention includes a link mechanism configured to be deployed in a first direction and retracted in a second direction opposite to the first direction, a plurality of front wing covers (180) mounted on a front side which is one side of the link mechanism perpendicular to the first direction, and a plurality of flight feathers (160) mounted on a rear side which is the other side of the link mechanism perpendicular to the first direction, wherein the front wing covers (180) and the flight feathers (160) are streamlined from the front side toward the rear side, and when the link mechanism is retracted, the flight feathers (160) are retracted inside the adjacent flight feathers (160).

Abstract: A wing having a main wing and a high lift assembly with a body and a connection. The connection movably connects the body to the main wing, such that the body is movable between a retracted position and at least one extended position. The connection comprises a track extending along a longitudinal axis between a first end and a second end and an intermediate portion between the ends. The first end and/or the intermediate portion is mounted to body, and the second end and/or the intermediate portion is mounted to the main wing by a roller bearing such that the track is movable along the longitudinal axis. The roller bearing has a roller unit mounted to the main wing and engaging a surface provided at the track so that the roller unit can adapt its tilt position with respect to the surface.

Abstract: A wing for an aircraft is disclosed including a main wing and a trailing edge high lift assembly having a flap, and a connection assembly movably connecting the flap to the main wing, such that the flap is movable between a retracted position and at least one extended position, wherein the connection assembly includes a support element that is mounted to the flap and that is movably mounted to the main wing, such that the support element is movable relative to the main wing along a predefined path between a stowed position and a deployed position. The support element is formed as an elongate support beam that extends along a beam longitudinal axis between a front end and a rear end and has an intermediate portion between the front and rear ends.

Abstract: An assembly for an aircraft turbine engine is provided. The assembly generally includes an un-ducted propeller blade of which the root has a bulbous portion; a system for setting the pitch of the blade about a pitch setting axis, the pitch setting system including a cup configured to be placed inside the outer casing, has a flared open top end for axial insertion of the root and in which the root of the blade can be axially affixed by a locking member; and at least one radial retention prong in a radial space reserved between the wall of the cup and the root.

Abstract: The propeller described herein may increase the pressure differential to be generated at/near a blade tip and, at least in some embodiments, to allow for the greatest pressure differential to be generated at/near the blade tip. Increasing the pressure differential in the blade tip region may promote formation of blade tip vortices when the propeller is in use. The propeller may utilize these blade tip vortices as effective mass flow, which can contribute to the thrust force generated by the propeller. That is, by designing the propeller to form and utilize blade tip vortices, the mass flow of air over the blades may be increased, thereby increasing the amount of thrust generated by the propeller.

Abstract: A collective pitch adjustment mechanism for a variable-pitch rotor that has blades for rotation about a rotor axis, e.g., for a flight vehicle or drone, via a motor. The mechanism has a servo actuator and a bearing cage for blade rotation. The servo actuator varies the collective pitch of the blades via a pushrod, and a servo actuator arm is configured for rotation and connected to the pushrod via a joint. Mounting portions are provided for securement of the blades and an actuation horn is coupled to the pushrod. The blades are rotationally and/or translationally coupled to the actuation horn via the mounting portions. The servo actuator causes rotational movement of the servo actuator arm, which in turn causes translational movement of the pushrod, which causes linear movement of the actuation horn to thereby collectively cause a collective change in a pitch angle, i.e. the collective pitch, of the blades.

Abstract: A rotor assembly includes a first rotor, a second rotor and a damper system. The first and second rotors are arranged to be rotated about a common axis for thrust generation by a drive system. The first rotor is rotatable about the common axis relative to the second rotor between a stowed configuration of the rotor assembly in which a rotor blade of the first rotor and a rotor blade of the second rotor are substantially angularly aligned and a deployed configuration in which the rotor blade of the first rotor and the rotor blade of the second rotor are angularly misaligned. The damper system is arranged to generate a damper force opposing the relative rotation between the first and second rotors in at least one of the direction towards the stowed configuration and the direction towards the deployed configuration.

Abstract: A drive mechanism, a drive system and an aerodynamic structure for an aircraft, each including at least one articulated module comprising four links. Each link includes three coupling points distributed forming a triangular geometry. The links are coupled to each other such that an articulation with only one degree of freedom is provided.

Abstract: This aircraft flight trim system comprises a friction module that has variable friction and is coupled on one side to a drive shaft and on the other side to an output shaft via a kinematic chain. It has a control circuit which controls the friction module on the basis of an angular displacement value of the output shaft provided by a position sensor and on the basis of a force feedback control signal provided by a flight control computer.

Abstract: Systems and methods for a gyroscopic rotational wing for an aircraft are disclosed. In one embodiment, a safety and stability device for an aircraft comprises an inner ring, an outer ring that rotates relative to the inner ring, and a motor connected to the inner ring that drives rotation of the outer ring relative to the inner ring. In some embodiments, the safety and stability device rotates in a substantially horizontal plane and at a rotational speed sufficient to provide gyroscopic stability for the aircraft.

Abstract: An aircraft includes a fuselage body extending in a front-rear direction; a tail wing at a rear portion of the fuselage body in the front-rear direction; a main wing in front of the tail wing in the front-rear direction on the fuselage body; and a fan device on an outer surface of the fuselage body. The fan device includes a rotor shaft outside the outer surface of the fuselage body, a rotor blade on an outer side of the rotor shaft in a rotor radial direction with the rotor shaft as a center, a housing fixed to the fuselage body, extending in the front-rear direction, including respective openings at a front and a rear in the front-rear direction, and provided to cover the rotor shaft and the rotor blade, a stator blade.

Abstract: A universal-joint cross assembly includes a cross. Four compression rings are mounted at terminal positions of the cross. Each of the four compression rings is positioned at a 90° interval relative to adjacent ones of the four compression rings. The universal-joint cross assembly includes four inner balls. Each of the four inner balls is fixed to one of the four compression rings and forms a portion of a spherical bearing.

Abstract: Aspects of the present invention relate to unmanned aerial vehicle launch technologies and methods for receiving at a head-worn computer (HWC) a plurality of images captured by an unmanned aerial vehicle (UAV) launched from a grenade launcher, and displaying the plurality of captured images in a sec-through display of the HWC.

Abstract: A system for providing a beverage in an aircraft, as well as a galley system comprising a first and second trolley, and an aircraft. The system comprises a first and second trolley, the second trolley detachably couplable to the first trolley via a coupling arrangement. The first trolley comprises a water tank fluidly connected to an outlet arrangement, and the second trolley comprises an inlet arrangement, a dispenser outlet, and a fluid conduit to permit fluid flow between the inlet arrangement and the dispenser outlet. The outlet arrangement of the first trolley is fluidly connectable to the inlet arrangement of the second trolley, and at least one trolley comprises a fluid propulsion arrangement for moving a fluid from the water tank to the dispenser outlet such that the first trolley is couplable to the second trolley to provide a flow of water from the water tank to the dispenser outlet.

Abstract: A drainage device for a tank of an aircraft, comprising a drainage duct, a drainage valve positioned between the upstream and downstream ends of the drainage duct, a housing dimensioned to house at least the downstream end of the drainage duct and a hatch moveable between an open position and a closed position in which the hatch closes the housing. The hatch comprises a liquid store positioned on the inner face thereof, into which the drainage duct opens when the hatch is in the closed position. The liquid store collects and stores liquid coming out of the drainage duct in the event of leakage from the drainage valve. Also an aircraft with such a drainage device.

Abstract: A compressing device includes a first turbine a second turbine and a compressor. The first turbine is configured to provide a first energy by expanding a first medium and the second turbine configured to provide a second energy by expanding a second medium. The compressor is configured to receive the first energy and the second energy during a first mode of the compressing device, receive the first energy during a second mode of the compressing device, and compress the second medium in accordance with the first mode or the second mode.

Abstract: An example system includes a turbine comprising an input port and mechanically coupled to a motor-generator and a compressor and control circuitry configured to determine whether a pressure of a fluid at the input port of the turbine is less than or equal to than a threshold pressure. In response to determining that the pressure of the fluid at the input port of the turbine is less than or equal to the threshold pressure, the control circuitry is configured to cause the motor-generator to operate in motor mode. The motor-generator is configured to be mechanically coupled to the compressor, and the motor-generator is configured to provide mechanical energy to drive the compressor when operating in motor mode.

Abstract: Aspects of the present disclosure can be embodied in a systems for heating an exterior surface of a bulk medium. In one example, the system includes two or more coupling strips spaced apart from one another and attached to the bulk medium. Each of the coupling strips has a multi-layer structure extending along a surface of the bulk medium that forms, in combination with the bulk medium, an electrical transmission line. The multi-layer structure includes a first dielectric layer over the bulk medium, a conductive layer over the first dielectric layer, a second dielectric layer over the conductive layer, and a conductive shielding layer over the second dielectric layer. A power control system is coupled to the conductive layer of each of the coupling strips and to the bulk medium. The power control system is configured to heat the bulk medium by providing current to the coupling strips.

Abstract: An emergency evacuation system includes a first floatation device, an inflator operably coupled to the first floatation device, and a second floatation device coupled to the first floatation device. The inflator is configured to inflate the first floatation device to deploy the emergency evacuation system outside of a compartment, such as proximate to a door of a vehicle.

Abstract: The present disclosure provides a podded engine adaptor configured to secure a podded engine to an aircraft, comprising: an airframe mounting interface configured for attachment to an airframe of an aircraft; an engine mounting interface configured for attachment to an engine; wherein the podded engine adaptor is configured to be attached to an engine at the engine mounting interface and to an airframe of the aircraft at the airframe mounting interface, so as to indirectly couple an engine to the aircraft via the podded engine adaptor.

Abstract: A hybrid electric propulsion (HEP) system included in an aircraft includes a generator configured to output a first power, an energy storage system configured to output a second power, a propulsion system configured to generate thrust based on at least one of the first power and the second power, and an HEP controller in signal communication with the generator, the battery, and the HEP system. The HEP controller is configured to detect loss of the first power output from the generator, to determine an altitude of the aircraft and to actively control delivery of the second power to the propulsion system based on the altitude during the loss of the first power.

Abstract: According to the present invention there is provided an aerial vehicle that is operable to fly, the aerial vehicle having at least a first and second subsystem that are operably connected, wherein the first subsystem comprises a first flight module, first one or more effectors that are selectively operable to generate a first force sufficient to cause the aerial vehicle to fly; and the second subsystem comprises a second flight module, second one or more effectors that are selectively operable to generate a second force sufficient to cause the aerial vehicle to fly; such that the first or second subsystem can be selectively used to fly the aerial vehicle not relying on the one or more effectors of the other subsystem. There is further provided a corresponding method for controlling an aerial vehicle.

Abstract: The present disclosure provides an unmanned device control method and apparatus, a storage medium, and an electronic device. In the method, thrust force required for an unmanned device and a target rotation speed required for providing the thrust force to the unmanned device are determined according to state information and/or environment information of the unmanned device, a voltage inputted into a motor of the unmanned device is adjusted according to the target rotation speed, and the unmanned device is controlled by using an adjusted voltage.

Abstract: A thermal management system for battery includes a plurality of cells, at least one inlet element having main inlet conduit and a plurality of inlet rail conduits, at least one outlet element having a main outlet conduit and a plurality of outlet rail conduits, and a plurality of battery holders. Each battery holder of the plurality of battery holders includes: a hollow wall structure surrounding a cavity in which a respective cell of the plurality of cells is to be accommodated; an inlet orifice; and an outlet orifice. The thermal management system may further include a coolant configured to be received via the main inlet conduit into a respective inlet rail conduit, wherein the coolant is configured to: circulate through the cavity of the hollow wall structure and exchange heat generated by the respective cell; and flow via a respective outlet rail conduit to the main outlet conduit.

Abstract: A system for an aircraft including: a fuel tank defining an interior; and a fuel cell assembly having a fuel cell defining an air outlet, wherein the air outlet of the fuel cell is in airflow communication with the interior of the fuel tank for providing an inerting airflow from the fuel cell to the interior of the fuel tank to reduce an oxygen content of the interior of the fuel tank.

Abstract: A ram air turbine may include an output shaft, a first turbine blade set configured to rotate in a first direction, and a second turbine blade set configured to counter-rotate with respect to the first turbine blade set. The rotation of the first turbine blade set and the counter-rotation of the second turbine blade set drives the output shaft.

Abstract: A fluid accelerator including an outer housing having an inlet end and an outlet end, the outer housing defining a converging nozzle proximate the inlet end. The fluid accelerator may also include an annular ring disposed proximate the inlet end of the outer housing within the converging nozzle, wherein the annular ring has an airfoil cross-sectional shape.

Abstract: A turbine wheel may include an inner hub having a central axis, an outer ring concentric with the inner hub, and an intermediate ring concentrically disposed between the inner hub and the outer ring, and a plurality of turbine blades extending between the intermediate ring and the outer ring. The turbine blades may be oriented to be driven by a fluid stream flowing through the turbine wheel to rotate the turbine wheel in a first direction about the central axis. In addition, the turbine wheel may further include a plurality of compressor blades extending between the inner hub and the intermediate ring. Also, the compressor blades may be oriented to propel a fluid in a downstream direction when the turbine wheel is rotated in the first direction.

Abstract: A system for monitoring an aircraft fluid storage tank assembly is disclosed including a pressure sensor configured to receive an acoustic signal emitted from a location within the aircraft fluid storage tank assembly in use and a controller. The controller is configured to receive information indicative of the acoustic signal from the pressure sensor and perform a determination process to determine, on the basis of the received acoustic signal, whether to output an indicator of a fault condition of the aircraft fluid storage tank assembly.

Abstract: Systems and methods are provided for displaying horizontal situational indicator (HSI) for a vertical takeoff and landing (VTOL) aircraft. The system includes an aircraft control panel in a cockpit of the VTOL aircraft and a HSI digital display that is located on the aircraft control panel. The HSI digital display shows a fixed target symbol representing an intended landing point, a speed vector indicator that represents an approach direction and a predicted hover point relative to the fixed target symbol that is calculated based on the speed, acceleration and turn rate of the VTOL aircraft, and a dynamic target symbol representing a positional change in the predicted hover point in response to instantaneous dynamic changes in flight conditions for the VTOL aircraft.

Abstract: A method for producing a fuselage structural component for a triangle region of an aircraft by: providing an integral board of a former material, wherein the board has an opening; and deforming at least one internal edge of the board that forms the opening to an internal flange; and deforming at least one external edge of the board to an external flange. Adjacent to the opening, the integral and deformed board forms in each case a former portion, a floor beam and a vertical support. Also a fuselage structural component and an aircraft with the fuselage structural component.

Abstract: An automated clamp for clamping a rib web to a rib post or rib foot of an aircraft wing box is disclosed including a clamp frame having a first arm and a second arm extending from the base of the clamp frame. The second arm is moveable towards and away from the first arm; a robot end effector connector coupled to the clamp frame; clamp jaws including a first jaw fixed at a distal end of the first arm, and a second jaw fixed at a distal end of the second arm, the clamp jaws configured to clamp a rib web to a rib post or clamp a rib web to a rib foot. The first jaw and/or second jaw includes a contact normalisation system, the contact normalisation system including: a jaw body fixed relative to the respective arm.