Abstract: A linear extension attachable to the aft end of an existing pontoon boat, including a v-hull shaped portion behind an outboard, inboard, or inboard-outboard motor, with the keel of the v-hull shaped portion centered on a propeller of the motor, a pair of water directing tubes on each side of the v-hull shaped portion, a pair of outside walls on either side of the water directing tubes, and a set of board deflectors that extend vertically downward in order to create a phenomenon similar to “hydraulic jump,” thereby creating the surfing wave.

Abstract: Diving goggles having a detachable camera bracket includes a frame, a pair of lenses, and a mask. The lenses and the mask are mounted to the frame. The camera bracket is detachably mounted on the frame. A lower end of the camera bracket is secured to the frame by means of clipping and hooking, and an upper end of the camera bracket is provided with a retaining seat for mounting a camera. The camera bracket connects the camera with the frame stably. During diving, the diver can take a picture for the underwater scenery conveniently, enhancing the diving entertainment.

Abstract: Device for pressurized breathable gas for a diver, wherein the pressure reducing device (1) having a yoke (6) and includes a body (2) that houses a gas circuit (3) formed at the level of an inlet connection (9), a depressurized gas outlet, a pressure regulator (3) located between the inlet (4) and the outlet (5), a yoke (6) connected to the body (2) and supporting a clamping mechanism (7) that is mobile to the yoke (6) to for tightening or loosening of a pressurized gas source valve (8) at the inlet (4) of the body (2), the inlet connection (9) includes an upstream end around the inlet (4), the sealing region (100) includes a seal (10) and/or is designed to cooperate with a seal (10) of a valve or an adapter of a valve to seal between a valve (8) and the pressure relief device (1).

Abstract: A carriage arranged to walk along elongate member while carrying a payload includes individually-operable clamps that are spaced axially along a common longitudinal axis. An axially-extensible frame connects the clamps. At least one of the clamps is attached to the frame via a rotationally-displaceable coupling for relative angular movement between that clamp an the frame about the longitudinal axis. The carriage can carry the payload to a subsea worksite by opening and closing the clamps to release and grip the elongate member in a sequence that includes moving the leading clamp forward when the leading clamp is open and moving the trailing clamp forward when the leading clamp is closed. At the worksite, installation force can be applied to the payload in a forward direction by moving the leading clamp forward when the leading clamp is open and the trailing clamp is closed.

Abstract: The present invention provides a self-draining oil buoyancy regulating device for underwater robots, wherein the accumulator, lower hatch cover, hatch trunk, upper hatch cover and bladder are fixedly connected in sequence; the water-proof connector is fixed on the upper hatch cover; the depth-pressure sensor is settled on the lower hatch cover to check the underwater pressure; the upper valve block, hydraulic-operated check valve and lower valve block are connected though piping in sequence; the lower valve block is fixed on the lower hatch cover; the pump outlet pressure sensor and the accumulator pressure sensor are settled on the lower valve block; the directional valve and the upper valve block are connected through piping; the hydraulic pump motor assembly and the relief valve are both connected with the lower valve block through piping; the depth-pressure sensor, pump outlet pressure sensor and accumulator pressure sensor are all connected with the control panel; the control panel is connected with the

Abstract: A propeller unit of a marine propulsion apparatus includes: an inner hub; an outer hub arranged coaxially with the inner hub, connected to the inner hub, and provided with a plurality of blades on its outer circumferential surface; and a bushing having a hollow shaft member provided with ribs on an outer circumferential surface and connected to the propeller shaft, and a damper formed of an elastic member and arranged to cover an outer circumferential surface of the hollow shaft member between the outer circumferential surface of the hollow shaft member and the inner circumferential surface of the inner hub, wherein the bushing is spline-coupled to the propeller shaft through spline teeth formed on an inner circumferential surface of a front half or rear half of a longitudinal direction of the hollow shaft member, and has a breakable portion provided in a part corresponding to the non-spline-toothed portion.

Abstract: A motorized fin booster system for surfboard or paddleboard or recreational small craft, consisting of at least one detachable motorized fin and at least one external, contour conforming and waterproof power supply are disclosed. The disclosed system allows for the addition and removal of electrically powered boost to nearly any board without permanent alteration of the board. The system integrates with widely used surfboard components; such as surf fins, leashes, ankle cuffs, and traction pads.

Abstract: A rigging for a wind-propelled vessel includes: a rotating airfoil-shaped mast; a sail movably coupled to a trailing edge of the airfoil-shaped mast and configured to be hoisted or lowered along the airfoil-shaped mast; a swiveling masthead coupled to a top section of the airfoil-shaped mast; and a plurality of stays supporting the airfoil-shaped mast, each stay having a first end connected to the swiveling masthead and a second end connected to a hull of the vessel.

Abstract: An outboard motor includes a plurality of electric actuators including an electric steering actuator and an electric tilt actuator, a power-source voltage detector that detects a power-source voltage in the outboard motor, an ECU, and a memory. If a power-source voltage detected by the power-source voltage detector becomes lower than a predetermined threshold value and if the plurality of electric actuators are simultaneously driven, the ECU determines that a voltage variation event has occurred. Event information including the number of occurrences of the voltage variation event is recorded in the memory.

Abstract: An exhaust gas processing apparatus that processes exhaust gas, including a reaction tower that includes an internal space extending in a height direction; a trunk tube that extends in the height direction in the internal space of the reaction tower and transports a liquid; and a plurality of branch tubes that are provided extending from an outer side surface of the trunk tube toward an inner side surface of the reaction tower, each include an ejecting section that ejects the liquid supplied from the trunk tube, and are provided at positions at different heights. Ejection regions of the liquid where the liquid is ejected from the respective ejecting sections of branch tubes that are adjacent in the height direction include a region in which the ejection regions partially overlap in an overhead view as seen from the height direction.

Abstract: A system for operating a boat equipped with an electric drive includes a component controller. The component controller includes a component interface for connecting a system component of the electric drive, and a communication interface for connecting the component controller to a system bus of the drive control.

Abstract: The present invention relates to the technical field of UAV (unmanned aerial vehicle), and more particularly to a UAV with linkage foldable arms, which includes a linkage mechanism, a fuselage body and multiple aircraft arms. The multiple aircraft arms are connected with each other through the linkage mechanism and are connected with the fuselage body; a locating part is located in a middle of the fuselage body; the locating part comprises a positioning structure, a fixed structure which plays a limit role is located on one of the multiple aircraft arms, the fixed structure is buckled with the positioning structure. When the aircraft arms are unfolded or folded, only one aircraft arm needs to be operated to drive other aircraft arms to move under the action of the linkage mechanism, so that multiple folding steps are simplified into a folding process, which is convenient in operation and strong in practicability.

Abstract: A moisture control assembly for use with a support beam extending through an insulation layer is provided. The insulation layer is positioned between an outer wall and an inner wall. The assembly includes: a moisture path close-out structure coupled to the insulation layer at an aperture defined through the insulation layer, the moisture path close-out structure including an opening substantially aligned with the aperture and configured to receive the support beam therethrough; and a coupling mechanism configured to secure the moisture path close-out structure to the support beam such that the moisture path close-out structure is partially pulled away from the insulation layer, the coupling mechanism and the moisture path close-out structure configured to direct liquid flow down and away from the support beam and along the insulation layer.

Abstract: A laminated glazing includes a first structural ply assembled with a first glass sheet of 0.5 to 1.5 mm thickness by way of a first adhesive interlayer, the first glass sheet forming a first exterior face of the laminated glazing, the face of the first glass sheet oriented toward the first adhesive interlayer bearing a first conductive heating layer of 2 ?ngströms to 500 nm thickness, and the first conductive heating layer including flow-separating lines of 0.05 to 0.2 mm thickness spaced apart by 8 to 20 mm.

Abstract: A network system for monitoring and storing data of aircraft intelligent windows or windshields to provide useable life of, provide real life performance of, and/or measure characteristics and/or properties of, the windshields forwards the data from sensors mounting the windshield to a window sensing hub having a microprocessor programmed to receive and process the data to determine the performance of the windshield and formatting the data in accordance to a preset program, wherein the program includes providing data from the sensors that measures characteristics and properties of the windshield that are active during the period in which the data is taken. An aircraft central maintenance system connected to the window sensing hub receives the formatted information from the window sensing hub and unfiltered or unformatted information, wherein the unfiltered information from the windshield is acted on by the central maintenance system to provide an estimated useable life of the windshield.

Abstract: A thrust producing unit for producing thrust in a predetermined direction, comprising at least two rotor assemblies and a shrouding, each one of the at least two rotor assemblies, defining an associated rotor plane, wherein a first rotor assembly of the at least two rotor assemblies is provided for operating in a failure-free operating mode of the thrust producing unit and a second rotor assembly of the at least two rotor assemblies is provided for operating at least in case of a failure of the first rotor assembly, and wherein the shrouding accommodates at most one of the at least two rotor assemblies.

Abstract: A thrust producing unit for producing thrust in a predetermined direction, comprising a shrouding and at least two rotor assemblies, wherein the shrouding defines an internal volume, and wherein a first rotor assembly of the at least two rotor assemblies defines a first rotor axis and a second rotor assembly of the at least two rotor assemblies defines a second rotor axis, the first and second rotor axes being one of: (i) coaxially arranged, and (ii) inclined by associated inclination angles with respect to the predetermined direction, the associated inclination angles being comprised in a range between ?60° and +60°, and preferably amounting to 0°, and wherein the first rotor assembly is arranged outside of the internal volume of the shrouding.

Abstract: An aircraft is provided including a fuselage extending between a forward end and an aft end. An aft engine is mounted to the fuselage at the aft end of the fuselage. The aft engine includes a nacelle having a forward section. An airflow duct is also provided extending at least partially through the nacelle and including an opening on the forward section of the nacelle. The opening is configured for providing an airflow to, or receiving an airflow from, the forward section of the nacelle to increase an amount of, e.g., boundary layer airflow received within the aft engine during operation of the aircraft, to guide the flow of boundary layer airflow into the engine more smoothly, or to reduce a distortion on the engine.

Abstract: A semi-levered landing gear including a shock strut configured for coupling to an airframe of an aircraft, a truck lever being rotatably coupled to the shock strut, a tension link assembly having a tension link assembly first end, a tension link assembly second end and at least one tension link assembly rotation axis, the tension link assembly first end being coupled to the shock strut, and the tension link assembly second end being coupled to the truck lever, and a positioning mechanism configured for coupling to one or more of the airframe and the shock strut and being coupled to the tension link assembly, wherein the tension link assembly is configured to rotate the truck lever about the truck pivot axis of rotation between a truck lever extended position and a truck lever stowed position.

Abstract: The present invention relates to an actuator in a landing gear system of an aircraft, comprising: an electric drive for driving the actuator and first drive electronics for controlling the electric drive that are connected to the drive via an electric line, with second drive electronics for controlling the electric drive that are connected to the drive via an electric line, with the first drive electronics and the second drive electronics being redundant with respect to one another.

Abstract: A fault detection system for an aircraft braking system including: a controller configured to receive braking demand information; torque information; wear information; wheel speed information; and brake temperature information. The controller is to calculate an expected maximum temperature of the brake based on the torque information, the wear information and the wheel speed information; to determine whether a significant temperature discrepancy exists between the expected maximum temperature and the brake temperature information; to determine whether a significant torque-related discrepancy exists based on the braking demand information and the torque information.

Abstract: A rotor assembly includes a motor, a propeller, and a connection assembly. The motor includes a stator and a rotator rotatable with respect to the stator. The connection assembly includes a locking member provided between the propeller and the rotator. The locking member is configured to rotate with respect to the rotator and the propeller to lock the propeller to the motor.

Abstract: A plastic composite component which is formed by a thin hard plastic outer layer, at least one elastomer layer adjoining the former on the inside, and at least one metal and/or plastic carrier layer adjoining said elastomer layer on the inside and made of a fibre reinforced plastic (RFP). A carbon fibre reinforced plastic (CRP) or glass fibre reinforced plastic (GRP), is arranged on the component or at least partly forms the latter, as an impact protection part, as a splinter protection part, as a protective part against sudden total failure or as a protective part against vibrations and vibration damages, against resonance, for the purpose of damping oscillations or for the purpose of acoustic damping.

Abstract: An emergency collective actuator includes an actuator motor to produce an actuation force and an actuator linkage that directly engages a friction control lever that is pivotally supported on the collective stick of a helicopter to apply the actuation force directly to the friction control lever such that the actuation force initially disengages the friction control and then reduces the adjustable pitch toward a minimum collective pitch position. The actuator can include a clutch that slips to allow the pilot to overcome the actuation force and that slips responsive to an engagement of the friction control by the pilot, but otherwise the clutch co-rotates with the motor shaft to bias the adjustable pitch toward a minimum collective pitch position.

Abstract: A VTOL aircraft having thrust and directional control comprises a fan for providing a centrifugal flow of air. At least one duct allows for and directs air flow. At least one nozzle allows for exhaust release. Each of the at least one nozzle has a first end attached to one of each of the at least one duct. Each of the at least one nozzle has a turn measuring 90° and faces downward from the second end of each of the at least one duct. Each of the at least one nozzle has a second end at which is a vane for redirecting airflow. The VTOL aircraft also has an attachment for landing.

Abstract: Systems and methods include providing an aircraft with a flight control system, a hybrid electrical or hybrid hydraulic propulsion system, and three ducted fan configuration. Each of two ducted fore fans include a single rotor system having multiple rotor blades, and a single ducted aft fan includes dual, coaxial, counter-rotating rotor systems each having multiple rotor blades. The aircraft is a vertical takeoff and landing (VTOL) aircraft that is capable of operation in an airplane mode and a helicopter mode and designed to provide an urban air-taxi that would relieve ground traffic congestion, reduce carbon emissions, and increase productivity, thereby providing a faster, more efficient means of transportation.

Abstract: Heavier-than-air, aircraft having flapping wings, e.g., ornithopters, where angular orientation control is effected by variable differential sweep angles of deflection of the flappable wings in the course of sweep angles of travel and/or the control of variable wing membrane tension.

Abstract: A cleaning apparatus for cleaning façades includes an aerial vehicle with rotors and a cleaning device attached to the aerial vehicle. This cleaning device can clean façades easily, mechanically with brushes or with a cleaning medium such as for example deionized water or dry ice.

Abstract: A solar cell module for an unmanned aerial vehicle is disclosed. The solar cell module includes a carrier base and a solar cell unit. The carrier base is disposed on the unmanned aerial vehicle. The solar cell unit has a plurality of solar cells attached to the carrier body. A ratio of the power provided by the solar cell unit to the weight of the solar cell module is equal to or greater than 0.1 (W/g).

Abstract: An unmanned aerial vehicle includes a fuselage, a power device connected to the fuselage, and a control device disposed at the fuselage and electrically connected with the power device. The control device is configured to control the power device to switch an operating mode of the power device to cause the unmanned aerial vehicle to fly in air or navigate on a water surface.

Abstract: A mobile, powered monitoring system includes an array of solar panels, a battery bank of at least one battery electrically connected to the array of solar panels, a landing and connection platform electrically connected to the battery bank, a cable electrically connected to the landing and connection platform, a drone electrically and mechanically connected to the cable, the drone having at least one camera, and a transmitter to allow images captured by the camera to be sent to a base station.

Abstract: An aerial system having an obstacle detection and avoidance system is described herein. The obstacle detection and avoidance system includes a pair of ultra-wide angle lens cameras orientated coaxially along an optical axis. Each ultra-wide angle lens camera includes a field-of-view lens having a vertical angle of view greater than 180 degrees. The pair of ultra-wide angle lens cameras is orientated such that a portion of each corresponding camera field-of-view overlaps to define a viewable region of interest including overlapping vertical field angle.

Abstract: A personal propulsion device, including a platform configured to support a passenger; a first thrust system coupled to the platform, wherein the first thrust system is configured to provide movement in a first direction; a second thrust system coupled to the platform, wherein the second thrust system is configured to provide movement in a second direction that is substantially perpendicular to the first direction; and a controller in wireless communication with the second thrust system, wherein the controller is configured to (i) measure an angle of tilt of the controller, and (ii) adjust an output of the second thrust system based at least in part on the measurement.

Abstract: A monument has a connection device, a fluid source and a compartment for the installation of a modular unit. The connection device is intended for connecting the fluid source to a modular unit installed in the compartment. The connection device includes two line sections. It is connected to the fluid source via one line section and can be connected to a modular unit via the other line section. The connection device is arranged so as to be displaced in the compartment on a predefined track between a connection position and an operating position. In the connection position the connection device is further from the rear end of the compartment than in the operating position. The connection device can be connected, in the connection position, via the second line section to a modular unit arranged outside the compartment. Also described is a system including a monument and a modular unit.

Abstract: A cabin segment for a vehicle includes a first lateral segment module having a first main extension axis, a second lateral segment module having a second main extension axis, and an aisle arranged in the cabin segment. The main extension axes parallel to each other, and the first and second lateral segment modules are distanced from each other in a direction perpendicular to the main extension axes and enclose the aisle, which runs parallel to the main extension axes. At least one of the first lateral segment module and the second lateral segment module includes a lavatory accessible through a lavatory opening positioned outside the aisle. The first lateral segment module includes at least one receiving space to receive serving trolleys. The at least one receiving space has a receiving opening facing into the aisle.

Abstract: A sleeping box for installation in an aircraft includes a casing which is suitable for accommodating a person located in a reclining position parallel to a longitudinal axis of the casing and which has an access aperture in the area of a front side which extends perpendicularly to the longitudinal axis of the casing. The sleeping box also includes a fastening apparatus which is configured to fasten the sleeping box within a passenger cabin of the aircraft in such a way that the longitudinal axis of the casing extends perpendicularly to a longitudinal axis of the passenger cabin and the access aperture of the casing borders on an aisle which is present within the passenger cabin.

Abstract: An interior space for an aircraft includes a cockpit, a cockpit wall separating the cockpit from the remaining interior space, a cabin door arranged directly behind the cockpit wall for accessing the interior space of the aircraft from outside the fuselage, a modular installation space for installation equipment, a plurality of seat rows, a longitudinal aisle extending along the interior space through the seat rows to separate adjacent groups of seats from each other, and an access path for the cabin door. The access path extends from the cabin door to the longitudinal aisle to create an intersection region between the access path and the longitudinal aisle. The modular installation space is arranged directly forward of the seat rows. The access path extends at an angle of at least 100° to the longitudinal aisle in a forward direction.

Abstract: A cabin arrangement for a vehicle includes a first lateral segment module having a first main extension axis, a second lateral segment module having a second main extension axis, and an aisle. The main extension axes run parallel to each other, wherein the first lateral segment module and the second lateral segment module are distanced from each other in a direction perpendicular to the main extension axes and enclose the aisle between each other. The aisle runs parallel to the main extension axes, and the first lateral segment module has a receiving space that receives serving trolleys. The receiving space has an opening that faces into the aisle. The receiving space is designed to receive serving trolleys arranged transverse to the first main extension axis and staggered parallel to the first main extension axis.

Abstract: A safety belt is intended to be installed on an aircraft seat and includes a first part and a second part which are able to be joined together by means of a buckle to hold the passenger on the seat. The safety belt may also include a status detection system able to transmit information relating to the fastening status of the safety belt, a presence detection system able to transmit information relating to the presence of a passenger wearing the safety belt, and/or a communications module, notably wireless, able to transmit information relating to the fastening of the safety belt and/or to the presence of a passenger wearing the safety belt.

Abstract: An adjustable vehicle seat includes a seat frame forming a seat back, the seat frame being configured to couple with an aerospace vehicle; a seat pan coupled to the seat frame, where one or more of the seat frame and the seat pan is configured to couple the seat pan to the seat frame in one of a plurality of positions relative to the seat frame so that an eye position of a seat occupant relative to instrumentation within the aerospace vehicle is decoupled from a size of the seat occupant.

Abstract: A galley cart includes walls defining an interior cavity extending between a front and a rear of the galley cart and the interior cavity extending between a top end and a bottom end. A supply port is provided in flow communication with the interior cavity at or near either the top end or the bottom end of the cart. A return port is provided in flow communication with the interior cavity that is adjacent the supply port at or near the top end or the bottom end of the cart. A barrier is positioned between the supply port and the return port within the interior cavity of the cart to define a supply chamber and a return chamber to control airflow through the interior cavity.

Abstract: A photovoltaic-based integrated power system for aerial vehicles includes (1) an integrated power management, regulation, and distribution (PMRD) subsystem including a case having an opening, (2) a case for the PMRD system, and (3) a flexible lightweight photovoltaic module capable of being applied conformally onto one or more aerodynamic surfaces.

Abstract: The present invention relates to an aircraft comprising a fuselage and a thruster downstream of the fuselage. The thruster includes a power turbine, located inside a main flow jet, and at least one fan, located inside a secondary flow jet and mechanically driven by the power turbine. The main flow jet of the power turbine and the secondary flow jet of the fan are concentric. The power turbine is supplied with gases from two gas turbine gas generators via two supply channels. Said aircraft is characterized in that said gas turbine gas generators have axes parallel to that of the fuselage. The air inlet sleeve is spaced apart from the fuselage, and the supply channels each have a hatch for controlling the flow between a position for guiding the gas flow to the power turbine and a position for ejecting the gases into the atmosphere while bypassing the power turbine.

Abstract: An air intake system (AIS) has a plenum and an inlet barrier filter associated with the plenum, through which air can selectively enter the plenum. The AIS also has an inlet duct associated with the plenum, through which air can selectively enter the plenum. The AIS also has a bypass door associated with the inlet duct, the bypass door being configured to selectively change an amount of air allowed to pass through the inlet duct. The AIS also has a filter airflow change device configured to change an amount of airflow allowed through the inlet barrier filter.

Abstract: Gas-flammability sensing systems and methods may be used to determine the flammability of gas mixtures in measurement volumes such as a fuel tank (e.g., an aircraft fuel tank). Gas-flammability sensing systems include a test cell structured to receive a gas sample, a heater in thermal communication with the test cell, and a gas meter configured to measure a physical property of the gas sample within the test cell related to the combustion state of the gas sample. The heater is configured to heat the gas sample to an elevated temperature less than the autoignition temperature of the gas sample. Methods of determining the flammability of a gas sample include collecting the gas sample, heating the gas sample to the elevated temperature, measuring the physical property of the gas sample after heating, and determining the flammability of a gas sample based upon the measured physical property.

Abstract: A system for providing an aircraft with protection against hard landings, the system comprising friction energy absorber systems arranged at the points the aircraft will impact against the ground in the event of a crash. The friction energy absorber system has two energy absorber devices arranged between a base and a cover along two non-parallel deformation axes, a support secured to the base and suitable for moving in translation relative to the cover, and a friction device. The friction device is arranged between the cover and the support and it generates a friction force along a translation axis parallel to a deformation axis such that the energy absorber device, after being plastically deformed during a crash, remains in contact with the support and the cover.

Abstract: A disruption device for fixing to an aerial vehicle. The disruption device is adapted to disrupt at least one radio path between at least one receiving unit of an unmanned flying body and at least one transmitting unit provided for controlling the flight path of the unmanned flying body. An aerial vehicle having the disruption device is further provided.

Abstract: There is provided an aeronautic vehicle including a first engine capable of providing propulsion and pressurising air and an environmental control system. The environmental control system includes an electrically powered compressor capable of pressurising air and a first pressurised air powered environmental control system pack. The environmental control system is configurable to provide pressurised air from the first engine to the first environmental control system pack, and the environmental control system is configurable to a ground configuration in which pressurised air is provided from the electrically powered compressor to the first environmental control system pack. There is also provided an environmental control system for an aeronautic vehicle and a method of operating an environmental control system of an aeronautic vehicle.

Abstract: A method includes making a first structure with a first plurality of pre-drilled holes at pre-defined locations, making a second structure with a second plurality of pre-drilled holes at pre-defined locations, making a third structure without pre-drilled full-size holes, measuring the location and orientation of the first and second plurality of pre-drilled holes in the first and second structures, determining the location of a third plurality of holes to be drilled in the third structure that correspond to first and second plurality of pre-drilled holes measured in the first and second structures, creating a program to drill the third plurality of holes in the third structure that align with the measured location and orientation of the first and second plurality of pre-drilled holes in the first and second structures based on the measure location and orientation of the first and second plurality of pre-drilled holes in the first and second structure, drilling the third plurality of holes in the third structu

Abstract: In order to improve and facilitate shimming between two parts, a deformable shim is provided that comprises a main structure of an at least partly cellular region. The main structure is compressible by plastic deformation from an initial volume to a deformed volume, wherein the deformed volume is smaller than the initial volume. In a deformed state, the main structure maintains the deformed volume without further or continuing compression force. Further, the main structure is arrangeable between a first aircraft component and a second aircraft component to create a predefined distance between the first and the second aircraft component.