Abstract: An electric-motor-assisted bicycle includes a vehicle-body frame and a drive unit including two couplers. The vehicle-body frame includes a bracket and a pair of chain stays. The drive unit is attached to the bracket. Each of the chain stays is attached to a position on the bracket rearward of a crank axle in the front/rear direction of the bicycle. One coupler is forward of the crank axle in the front/rear direction of the bicycle. The other coupler is rearward of the crank axle in the front/rear direction of the bicycle. At least one of a region of the bracket to which the chain stay is attached and a region of the bracket to which the other coupler is attached does not overlap a line segment connecting a shaft center of the axle of the rear wheel to a shaft center of the crank axle.

Abstract: In an electric-motor-assisted bicycle, a motor includes a motor output shaft including a helical gear provided thereon. A reduction gear includes a rotatable shaft and a cylindrical portion. The rotatable shaft extends through the cylindrical portion. A helical gear provided on the cylindrical portion engages the helical gear on the motor output shaft. The rotatable shaft includes a first large-diameter portion, a small-diameter portion and a second large-diameter portion. The reduction gear further includes a bush bearing between an end surface of the first large-diameter portion and an end surface of the second large-diameter portion in the axial direction of the rotatable shaft. The outer periphery of the bush bearing is fixed to the cylindrical portion. The inner periphery of the bush bearing slides in a circumferential direction relative to the small-diameter portion. The bush bearing moves in the axial direction.

Abstract: In a drive unit in an electric-motor-assisted bicycle, as viewed in an axial direction of the crank axle, a substrate housed in a housing does not overlap a reduction gear but overlaps a driven gear. The substrate is disposed around the crank axle and includes a component side extending in a direction crossing the central axis of the crank axle. The substrate extends in directions crossing radial directions of the crank axle. One end of the substrate in the direction in which the substrate extends is located on the side of the straight line connecting the shaft center of the crank axle and the shaft center of the motor output shaft as viewed in the axial direction, that is opposite to the side having the other end of the substrate in the direction in which the substrate extends.

Abstract: A bicycle includes an electrical auxiliary drive, including an electric motor, a battery for storing electrical energy, which battery is connected to the electric motor, a crank mechanism having pedal cranks, which are mounted on a pedal crankshaft disposed about a crank axis, so as to be able to rotate, and a planetary gear for driving the bicycle both by the electric motor and by the muscle power of a driver, the planetary gear and the electric motor being disposed about the pedal crankshaft of the crank mechanism.

Abstract: A bicycle transmission apparatus comprises a base member, a first transmission member, a second transmission member, a first coupling member, a first guide structure, a switching device, and a transmission controller. The switching device is configured to switch a position of the first transmission member relative to the base member in an axial direction between a first axial position and a second axial position. The transmission controller is configured to control the switching device and the first guide structure so as not to change a first engagement state of the first coupling member from one cogwheel to another adjacent cogwheel among first cogwheels when the first transmission member moves relative to the base member in association with a movement of the first guide structure relative to the base member to change a second engagement state of the first coupling member from one cogwheel to another adjacent cogwheel among second cogwheels.

Abstract: A system is provided and includes a trim tab, a hinge assembly, an actuator, and a controller. The trim tab adjusts at least one of pitch, roll or yaw motion of a marine vessel while the trim tab is in a deployed state. The trim tab includes a member, which has first and second ends and curves outward between and forward of the first end and the second end in a direction away from a point rearward of the member. The hinge assembly attaches a rearmost end of the first trim tab to the marine vessel at a location rearward of the member. The member rotates about a portion of the hinge assembly. The actuator actuates the trim tab. The controller controls the actuator to transition the member of the trim tab between a retracted state and the deployed state to adjust an attitude or motion of the marine vessel.

Abstract: A battery system for providing electric power to a boat includes a hard deck that includes a plurality of interconnected battery panels and output power connectors. Each of the battery panels includes an array of interconnected battery cells. A connection plate receives recessed edges of adjacent battery panels and interconnect cables connect battery terminals of the adjacent battery panels.

Abstract: A chain stopper is connectable to a support structure, such as a platform, and comprises: a chain locking portion for automatically engaging a first chain link of a chain so as to prevent the chain from being pulled in a first direction and; an activation portion connected to the chain locking portion. The activation portion is configured such that, upon pulling the chain in a second direction, the activation portion is adapted to be engaged by the chain so as to disengage the chain locking portion from the first chain link, allowing the chain to be pulled in the second direction.

Abstract: A flotation system includes one or more floatation modules, each having a first section and a second section, each having an internal core made of a buoyant material. The first section includes two end faces and a projection extending from one of the end faces. The projection has a contoured profile. The second section includes two end faces and a reciprocal recess in one of the end faces. The end faces of the first section engage the end faces of the second section such that the projection engages the reciprocal recess in a mating engagement. A stop collar may be disposed adjacent each end of the floatation module. The floatation system may be attached to a tubular string that is lowered into a marine riser to reduce a load applied to a rig disposed over the marine riser.

Abstract: According to the invention a semi-submersible vessel including a semi-submersible platform body is provided. The semi-submersible platform body is adapted to float in a body of water wherein the platform body comprising a plurality of pontoons arranged together to form a triangular structure, a plurality of columns having a lower portion and an upper portion, the columns extending outwardly from each corner of the triangular structure, wherein each column is triangular. Further, the semi-submersible vessel includes a deck supported by the upper portion of the columns.

Abstract: A standup paddleboard outrigger includes a long, narrow, lightweight displacement hull and a pair of outrigger pontoons mounted to a bridge. The two parts disengage for easy storage and transport. The hull has a platform to stand on. Paddling with a long handled paddle propels the craft through the water. The outriggers provide lateral stability/support and actuate the rudder in order to make turns. When a person stands on the platform and shifts body weight, the rudder will rotate to the right and the craft will turn to the right. The more weight that is shifted, the greater the turning action. The responsiveness to the shift of body weight can be adjustable for personal preference either firmer or more flexible, as is the turning response of the rudder fine or coarse turning.

Abstract: A single support stake surfboard support for elevating surfboards above a sandy beach. An elongated, hollow support stake, typically having a diagonal cut at its distal end to facilitate pressing the support stake into sand or other terrain. A T-support arm is removably, frictionally attached to a proximal end of the hollow support stake. In a first embodiment, cylindrical polymer cushions are disposed along the T-support arm. In the first embodiment, one or more surfboards may be laid flat across the pair of supports. In a second embodiment, at least two upwardly projecting members are attached to the distal and proximal ends of the T-support arm. Each of the upwardly projecting members may also have one or more cylindrical polymer cushions thereupon. In the second embodiment, up to four surfboards may be accommodated on edge between the upwardly projecting members.

Abstract: A suspension system for a multi-hulled vessel including: a chassis and at least one left hull and at least one right hull; a front left, a back left, a front right and a back right support arrangements with respective rams; a first adjustment accumulator having a fluid chamber and a gas chamber; and a first actuator to transfer or effectively transfer fluid between the fluid chamber of the first adjustment accumulator and at least one compression chamber of a respective ram of a first support arrangement comprising one or more of the front left, front right, back left or back right support arrangements. A static pressure in the gas chamber of the first adjustment accumulator being within 25% of a static operating pressure in the at least one compression chamber of the at least one ram of the first support arrangement.

Abstract: This invention relates to a submersible vessel for dry docking a vessel. The submersible vessel comprises a floating unit, a deck above the floating unit and a number of stabilising towers arranged on the deck. The deck has a base, a sidewall along a perimeter of the base and a block provided within the sidewall and resting on the base, defining a cavity such that when the vessel is being docked onto the deck, a thruster of the vessel is above the cavity.

Abstract: A lifesaving device and a lifesaving control method are provided. Wherein, the lifesaving device includes: at least one first detection module (200) configured for detecting human body biological characteristic information, a lifesaving device body (100) capable of being worn on a body of a user, and at least one first gasbag module (300) arranged on the lifesaving device body (100); after the first gasbag module (300) is activated, a lifesaving gasbag (1) can be popped up; the first detection module (200) is in signal connection with the first gasbag module (300) and is configured for activating the first gasbag module (300) when the biological characteristic information detected meets a first preset condition.

Abstract: An underwater vehicle designed for navigation at the surface or underwater, having a hull, and at least one normal-force generator of force normal to a longitudinal axis of the underwater vehicle, borne by the hull, wherein a forward part of the hull is asymmetric with respect to the longitudinal axis so as to generate lift as the underwater vehicle moves and wherein the lift is in the opposite direction to the resultant of the forces of the normal-force generator or generators is provided.

Abstract: The present invention discloses a method and device for controlling energy-saving sailing of a ship. The method comprises the steps of changing the operating parameters of the ship correspondingly when the resistance of the ship changes during routine sailing, controlling the current opening degree of a throttle to increase the instantaneous oil supply amount of a main engine of the ship if the resistance of the ship becomes smaller, and controlling the current opening degree of the throttle to reduce the instantaneous oil supply amount of the main engine of the ship if the resistance of the ship becomes larger. Compared with the prior art, the method and device have the advantages that energy waste is reduced greatly and the sailing cost is reduced.

Abstract: A protective device for a stern tube seal of a propeller-driven vessel, wherein an intermediate space is left open between a stern tube and a propeller hub, which intermediate space is covered by a tubular protective cover concentric with the propeller hub, which protective cover is fixedly anchored to the stern tube and axially overlies the propeller hub leaving an annular gap, wherein a ring concentric with the propeller hub and U-shaped in radial section is disposed inside the protective cover in the intermediate space between the stern tube and the propeller hub, the U-opening of which ring is directed radially outward, and wherein the ring is at least partially formed of a material that has a pourable consistency at 20° C.

Abstract: A watercraft drag apparatus may extend into the water from either the port or the starboard side of a watercraft or a hull of the watercraft. The drag apparatus may cause an increase in drag on one side of the watercraft. The increase in drag may slow the watercraft to a slower speed than the watercraft can typically maintain under normal power. The increase in drag may also cause the watercraft to change heading, requiring a watercraft pilot to repeatedly correct the heading to maintain an intended course. The watercraft drag apparatus may be useful for fishing, such as when trolling.

Abstract: Disclosed is an aerial vehicle such as an unmanned aerial vehicle (UAV). In one implementation, the vehicle includes a base and one or more front-facing arms extending from the base. Each front facing arm includes an inner segment affixed to the base and an outer segment. The vehicle also includes a rear-facing arm affixed to the base. In another implementation, a UAV includes one or more arms mounted to a base. At least one of the arms includes a first segment that is proximate to the base and a second segment that is distant from the base. A first hinge connects the first segment and the second segment. Various dimensions of the UAV are reduced when the arm(s) are folded along the first hinge.

Abstract: An arm-airframe connecting structure and an unmanned aerial vehicle are provided by embodiments of the present disclosure. The arm-airframe connecting structure is configured to movably connect an airframe and an arm, and the arm is switchable between an unfolded position and a housed position with respect to the airframe. The arm-airframe connecting structure includes: at least one arm matching part provided on the arm; and at least one airframe matching part provided on the airframe. The at least one arm matching part and the at least one airframe matching part are configured to be bonded with each other so as to maintain at least one of the unfolded position and the housed position of the arm with respect to the airframe.

Abstract: Aircraft antenna fairing assemblies include a fairing shell and connection components for positionally fixing the fairing shell to airframe structure of an aircraft. The connection components may comprise a guide assembly having a guide head and a receiver defining a guide channel for receiving the guide head therewithin, and a latch assembly for latching the fairing shell to the airframe structure of the aircraft. The receiver of the guide assembly may define a generally C-shaped or generally U-shaped channel for receiving the guide head therewithin.

Abstract: The invention relates to a propeller ring (10) of a turbomachine (1), with variable-pitch blades (P), the propeller ring (10) comprising a substantially coaxial annular body (11) with a main axis (A) and a plurality of radial housings (12) uniformly distributed around the main axis (A), each radial housing (12) being designed to receive a bearing (13) for a root (14) of a blade (P) so as to allow the variable pitch of the blade (P), the radial housings (12) having a substantially ovoid cross-section in a plane (T) tangential to the annular body (11).

Abstract: In order to simplify the design of an aircraft turbo engine propeller while enhancing the safety function thereof related to control of the blade angle of attack, a propeller is provided comprising a secondary rotational coupling to couple in rotation, along the radial axis of the blade, the inner radial end of the blade root with a mechanical joining member of a blade angle of attack control device, the secondary coupling being designed and configured to be active in the event of failure of the main pin.

Abstract: A blade pitch adjustment system comprising a yoke arranged to be moved in a first direction in response to an actuator; a plurality of trunnion pins arranged to be attached to a respective propeller blade; a respective contact surface between the yoke and each trunnion pin such that movement of the yoke causes rotation of the blades, and wherein the contact surfaces differ so as to create different angles of rotation of the blades at different points of yoke movement or actuator stroke.

Abstract: An hydraulic actuation control module is provided for installation in a pitch change actuator of a propeller assembly. The module comprises a flow metering valve arranged to supply hydraulic fluid flow and pressure to an actuator and an electronic control unit arranged to control the flow metering valve. The flow metering valve is arranged to meter hydraulic fluid flow and pressure to increase and decrease pitch chambers of the pitch change actuator, in accordance with the control of the electronic control unit. The flow metering valve is arranged to receive an hydraulic fluid supply from an entity relative to which the propeller assembly rotates such as an engine driving the propeller assembly or aircraft on which the propeller assembly is installed. A propeller assembly comprising the hydraulic actuation control module is also disclosed, together with a method of installing the module within a propeller assembly.

Abstract: A selector lever includes a detent pin that travels along a shaft for being positioned within a detent slot of a detent plate for securing the selector lever in place. A magnetic detent pin alignment mechanism provides feedback to an operator for assisting in maneuvering the selector lever to a predetermined position wherein the detent pin may be positioned within a desired detent slot.

Abstract: A device for releasably mounting an autopilot control circuit to a flight control component of an aircraft, includes a frame that holds a component of an autopilot control circuit; a first coupler releasably fastened to the frame and operable to releasably mount the frame to the airframe of an aircraft; and a second coupler releasably fastened to the frame and operable to releasably mount the frame to a flight control component of the aircraft. When the device is releasably mounted in an aircraft's cabin and the autopilot control circuit is engaged, the autopilot control circuit controls an aspect of the aircraft's flight by moving the second coupler relative to the first coupler. With the device one can releasably mount an autopilot control circuit to an aircraft that does not have one and use the autopilot control circuit and device to control one or more aspects of the aircraft's flight.

Abstract: A load detent assembly for restricting creep of a rotating assembly of an actuator used to actuate an aircraft flight control surface. The load detent assembly includes an engagement member having circumferentially spaced engagement surfaces/protruding portions, and a load detent having a stoppage member radially biasable towards the engagement member for interengagement between the engagement surfaces to restrict creep of the rotating assembly. One of the engagement member or the load detent is configured for rotation radially inward of the other of the engagement member or the load detent through at least 360 degrees of rotation. The other of the engagement member or the load detent is configured for being fixed radially outward of the one of the engagement member or the load detent.

Abstract: An aerial vehicle includes a hull containing the main processor, energy storage, support components such as sensors, wireless communication, and landing gear. Attached to the hull are at least three thrust or propulsion units each with two degrees of freedom from the hull allowing them to orient independently in any direction and apply thrust independently from the hull or any other thrust or propulsion unit. In some embodiments, a mount for auxiliary attachments is included or the auxiliary system is built into the hull. Components like the energy storage, auxiliary attachments, and/or propulsion units may also be replaceable as required.

Abstract: A fluidic system is disclosed. The system comprises a plurality of fluidic oscillatory actuators, and at least one synchronization conduit connecting two or more of the actuators such as to effect synchronization between oscillations in the two or more connected actuators.

Abstract: A device for reducing aerodynamic disturbances in the wake of an aerodynamic profile. The device comprises a first air ejection nozzle arranged on the top side of the profile and a second air ejection nozzle arranged on the underside of the profile. A first blowing chamber is fluidically connected to the first nozzle and a second blowing chamber is fluidically connected to the second nozzle. Air supply means are configured to vary the distribution of air between said first blowing chamber and second blowing chamber. The distribution of the blown air can thus be adapted depending on the situation in which the profile is used, for example depending on the flight phase of an aircraft equipped with such a profile. Also, an aerodynamic profile, a pylon supporting a propulsion assembly for an aircraft comprising such an aerodynamic profile, and an aircraft.

Abstract: A system for modifying a shock wave formed in a fluid by a body to modify effects of the shock wave on information transferred to or from the body. The system includes an element for heating fluid along a path to form a volume of heated fluid expanding outwardly from the path, the path extending from the body and through the shock wave; an element for transferring the information to or from the body; and an element for timing the transferring of the information relative to the heating of the fluid along the path to modify certain effects of the shock wave on the information.

Abstract: A rod end of an actuator assembly is disclosed. The rod end may comprise a rod piston end having an outer profile, and a rod joint end opposite the rod piston end, wherein the outer profile comprises an elliptical shape comprising a major diameter and a minor diameter, wherein the major diameter may be larger than the minor diameter in length.

Abstract: A kite for use in a system for extracting energy from the wind comprises: a wing (1) having a roll neutral point or zone when the kite is in flight; a tether (4) coupled directly or indirectly to the wing; a rigid spar arrangement (2); tensile couplings (3) from the spar arrangement to multiple locations on the wing; and an actuator linkage arrangement (6, 7, 10,11) having a length dimension that can be controllably adjusted. The spar arrangement has first and second attachments (8, 5) to the tether, at the first attachment (8) the spar arrangement is fixed to the tether at a location that is above a roll neutral point or zone of the wing, and at the second attachment (5) the spar arrangement is attached to the tether by the actuator arrangement (6, 7, 10, 11) at a location that is below the roll neutral point or zone of the wing.

Abstract: An aerial imaging system and method of aerially capturing an image including a first unmanned aerial vehicle (UAV) and a second UAV. The first UAV includes a camera and may be configured to receive input from an operator. The second UAV may be configured to dock with and deploy from the first UAV. The second UAV includes a light configured to provide remote illumination for the camera. The light on the second UAV may be activated to illuminate a target of photography by the camera while the second UAV is flown separate from the first UAV.

Abstract: An embodiment of the present disclosure provides an unmanned aerial vehicle, An unmanned aerial vehicle, with a double-layered structure formed by stacking a cover and a main component layer, wherein, the main component layer includes a base body and at least one functional component, the base body has a top facing to the cover layer and a bottom opposite to the top, the cover is in direct contact with the top of the base body, and the at least one functional component is mounted on the base body.

Abstract: An unmanned vehicle is provided. The unmanned vehicle includes: a base; a driving unit including an actuator and a propeller rotating by using power of the actuator, the driving unit being provided outside the base capable of pivoting with respect to the base; and a supporter protruding from the base and supporting the base.

Abstract: Power management method and system for an unmanned air vehicle, wherein the unmanned air vehicle comprises a plurality of power demanding subsystems and a plurality of power sources. The invention establishes mission oriented fixed parameters. A fuzzy logic power management unit, comprised in the system, automatically calculates and assigns priorities for delivering power to the subsystems. It also automatically calculates and assigns amounts of power delivered to each subsystem and automatically decides which of the power sources to deliver power to which subsystem. The fuzzy logic power management system calculates and assigns the priorities and loads in function of a plurality of internal variables, external variables and the mission oriented fixed parameters.

Abstract: An airship and method of providing thrust to an airship are shown. Examples include a number of turbine thrusters coupled to a number of electric motor/generators that supplement thrust from the turbine thrusters. Systems and methods are described that include surveying an agricultural area, and spraying an amount of an agricultural supply on only selected portion of the agricultural area.

Abstract: Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

Abstract: Systems and methods include UAVs that serve to assist carrier personnel by reducing the physical demands of the transportation and delivery process. A UAV generally includes a UAV chassis including an upper portion, a plurality of propulsion members configured to provide lift to the UAV chassis, and a parcel carrier configured for being selectively coupled to and removed from the UAV chassis. UAV support mechanisms are utilized to load and unload parcel carriers to the UAV chassis, and the UAV lands on and takes off from the UAV support mechanism to deliver parcels to a serviceable point. The UAV includes computing entities that interface with different systems and computing entities to send and receive various types of information.

Abstract: A system for moving loads comprising a cargo compartment floor, at least one roller track comprising rollers arranged one behind the other in the cargo compartment floor, at least one guideway in the floor and extending parallel to the at least one track, and at least one transport vehicle removably accommodated in and movable along the guideway. The transport vehicle comprises at least one connecting element movable between first and second operating positions. In the first operating position, the connecting element is configured so the transport vehicle is positionable beneath a load on the roller track, and in the second operating position, the connecting element is configured to interact with the load to connect the load to the transport vehicle, so the load is entrained when the transport vehicle moves along the guideway. The transport vehicle further comprises a drive mechanism to move the transport vehicle along the guideway.

Abstract: A stowage bin assembly is configured to be positioned above at least a portion of one or more seats within a vehicle. The stowage bin assembly may include a pivot bin including a forward end panel, an aft end panel that is opposed to the forward end panel, a front panel extending between the forward and aft end panels, and a closeout bracket secured to the forward end panel, the aft end panel, and the front panel. A baggage retaining chamber is defined between the forward end panel, the aft end panel, and the front panel. The closeout bracket spans between the forward end panel and the aft end panel.

Abstract: Avionics system for assisting implementation of security measures onboard an aircraft, aircraft comprising such a system, and associated method are provided. The avionics system is intended to assist the occupants of an aircraft in implementing security measures onboard the aircraft. It includes a parameter collector for collecting at least one avionics parameter of the aircraft, a context finder to determine a context from the or each avionics parameter collected by the collector, an instruction identifier to identify at least one relevant security instruction based on the context determined by the context finder, and at least one instruction submitter to submit the or each relevant security instruction to a passenger of the aircraft.

Abstract: There is described herein a method and system for the configuration of vehicle management components using in-vehicle position detection. The in-vehicle position detection may also be used for providing a floor plan of the vehicle. In some embodiments, in-vehicle position detection may be used concurrently for configuring vehicle management components and for providing floor plans.

Abstract: In order to improve ease of maintenance of an aircraft passenger seat, the aircraft passenger seat 100 is adapted to be changeable between an upright position and a bed mode position at which the backrest is folded forward. A mechanism for locking the seat at each of the positions is provided with lock pins 350 provided on both sides of the backrest, a handle unit 200 mounted to a rear face of the backrest, and two wires 300 for connecting the handle unit 200 and the lock pins 350. A structure for connecting the wires 300 to the handle unit 200 is improved to facilitate the maintenance of the wires and to make the handle unit lightweight.

Abstract: An ice prevention system is configured to prevent ice from forming and/or melt ice with respect to one or more portions of an aircraft. The ice prevention system includes a combustor having an air inlet and a gas outlet. A supply air conduit is coupled to the air inlet of the combustor. The supply air conduit is configured to channel low pressure air to the combustor. One or more delivery conduits are coupled to the gas outlet of the combustor. The delivery conduit(s) are configured to be coupled to the one or more portions of the aircraft. The combustor is configured to exhaust heated gas to the delivery conduit(s) through the gas outlet to prevent ice from forming with respect to the portion(s) of the aircraft.

Abstract: Apparatus and associated methods relate to determining liquid-water concentration in a cloud atmosphere based on a frequency of resonance of a magnetostrictive resonator and/or a temporal variation of the resonant frequency of the magnetostrictive resonator. The magnetostrictive resonator is configured to resonate at a resonant frequency indicative of a measure of ice accumulation upon an exterior surface of the magnetostrictive resonator. When in liquid-water ambient, however, the magnetostrictive resonator has a resonant frequency less than a baseline resonant frequency. When in the liquid-water ambient, the magnetostrictive resonator also has temporal variations in resonant frequency that exceed one part in ten thousand. Using one or both of these resonant-frequency responses to liquid-water ambient, a signal indicative of liquid-water content can be generated.

Abstract: To reduce the overall mass of an engine assembly for aircraft, this assembly comprises a part of the fuselage of an aircraft, a turbomachine comprising an unfaired propeller, together with an annular row of unfaired after-guide vanes located aft of the propeller and rotationally fixed in relation to a longitudinal axis of the turbomachine, and a mounting pylon. At least part of the leading edge of the pylon is incorporated within the annular row between two after-guide vanes.