Abstract: The application relates to a pedal mechanism and a housing of a balancing vehicle. The pedal mechanism comprises a pedal body, and an internal framework is arranged inside the pedal body. A lower side of the pedal body is also formed with an induction probe for inducting a control system inside a balancing vehicle. A housing of the balancing vehicle comprises a pair of symmetrically arranged and relatively rotatable inner housings, the inner housings are connected with the upper housing, and the pedal mechanism installed at upper housing. The pedal body and the induction probe are integrally molded, which has the advantages of less multiple assembly processes, shorter processing time, higher precision, and not easy to fall off which strengthens the stability of the structure.

Abstract: A foot and hand pedaled bicycle assembly that facilitates a full body working during riding includes a bicycle that has a front wheel, a rear wheel and a frame. The frame has a top member and a lower member that each pivotally extends between a seat post and a handlebar fork. The handlebar fork is urgeable toward or away from the seat post. A pair of pedals is provided and each of the pedals is rotatably coupled to the frame for rotating the rear wheel. A pair of hand cranks is provided and each of the hand cranks is coupled to the handlebar fork for steering the bicycle. Moreover, each of the hand cranks is in mechanical communication with the front wheel for rotating the front wheel when the hand cranks are cranked.

Abstract: A bicycle pedal assembly includes a crank arm, one end of which is pivotally connected to a propulsion axle of a bicycle and another end of which is pivotally connected to a first pivot at one end of an auxiliary crank arm. A pedal is connected to another end of the auxiliary crank arm and a pedal tilt limiter is coupled to the pedal and configured to limit tilt or rotation of the pedal.

Abstract: In a drive system of an electric assisted bicycle, a controller includes a vehicle speed calculator to calculate a change gear ratio of a change gear mechanism based on an output signal of a vehicle speed sensor and an output signal of a rotation sensor in response to acquisition of the output signal of the vehicle speed sensor, and calculate a vehicle speed based on the calculated change gear ratio and the output signal of the rotation sensor at a higher frequency than a frequency of the acquisition of the output signal of the vehicle speed sensor. The controller includes an initial target calculator to calculate target power without using the output signal of the vehicle speed sensor in a prescribed period from start of walking, when a walk command is received, and a target calculator to calculate a target power based on the vehicle speed calculated by the vehicle speed calculator after a lapse of the prescribed period.

Abstract: A human-powered vehicle control device for a human-powered vehicle includes an electronic controller configured to control a motor, which applies a propulsion force to a human-powered vehicle, in correspondence with a human driving force input to the human-powered vehicle. The electronic controller is configured to control the motor so as to increase an assist force produced by the motor for when an output of the motor is maximal upon determining a parameter related to at least one of a vehicle speed of the human-powered vehicle, an inclination angle of the human-powered vehicle, and a travel resistance of the human-powered vehicle has increased.

Abstract: A human-powered vehicle component includes a housing and a joint provided on the housing and configured to be attached to a support of the human-powered vehicle by a fastener. The joint includes a metal base, a metal coupling portion provided on the base and coupled to the fastener, and an intermediate portion provided between the coupling portion and the base. The base includes a first material having a first standard electrode potential. The coupling portion includes a second material having a second standard electrode potential. The intermediate portion is formed by a third material having a third standard electrode potential or a fourth material having an electric insulating property. A difference of the third and first standard electric potentials and a difference of the third and second standard electrode potentials are each smaller than a difference of the first and second standard electrode potentials.

Abstract: An ebike comprises a front wheel, a rear wheel, a frame structure supported on the front wheel and the rear wheel, a crank assembly, and a battery assembly. The frame structure can include a front fork supported on the front wheel, a head tube coupled to the front fork, and a down tube extending downward and rearward from the head tube, the down tube defining a down tube axis and being open at its lower end. The crank assembly can be supported by the frame structure and can be rotatable about a crank axis that is spaced rearward from the down tube axis. The battery assembly can be at least partially secured in the down tube in an installed position and can be slidable into the down tube from the lower end of the down tube along the down tube axis.

Abstract: A method for improving a fluid dynamic profile and fouling properties of a marine vessel with a welding seam which forms a cap protruding above a surface being under the waterline of a vessel. The method comprising amending the welding seam by applying a fairing to the underwater surface, e.g. by use of filler. A vessel with a fairing, and a coating system for a vessel and including a fairing.

Abstract: A foil system is used with a towed marine cable array to provide downward, upward or lateral lift to the array. The foil system can be coupled with the cable and configured to bias the submerged payload toward a target position. The foil system can include a group of foil sections each having a leading edge collectively defining an angle of attack, and a group of through-cables supporting the group of foil sections within the foil system. A subset of through-cables of the group of through-cables are arranged through front halves of the group of foil sections. This subset of through-cables can be selectively tensionable, and manipulatable to define a tensioned one of the subset of through-cables as being offset from a chord that is defined between the leading edge and a trailing edge of any of the foil sections. The foil system can thus induce one or more angles of attack for the group of foil sections, based on a rotational constraint defined by the tensioned one of the through-cables.

Abstract: Embodiments of an underwater monitoring system are provided. In one embodiment, the system has an anchor stake connected to a vented pipe. The pipe has an interior and an exterior and is configured to house a sensor in the interior. The vents on the vented pipe are configured to exchange water between the interior and the exterior while protecting any interior sensors.

Abstract: A personal watercraft includes: a watercraft body made of a resin; a handle projecting upward from the watercraft body; a meter display device disposed above the watercraft body and forward of the handle; a meter cover made of a resin and covering a space from above, the space being adjacent to and forward of the meter display device and being in contact with an upper surface of the watercraft body and a forward surface of the meter display device; and an antenna disposed in the space.

Abstract: The present application discloses an automatic water surface skimmer, belonging to the technical field of water surface cleaning. For the existing anti-collision structure, most of impact force is transmitted to a hull through an anti-collision wheel, resulting in that the anti-collision wheel and the hull are damaged, the anti-collision effect is poor, and the service life of the anti-collision wheel and the hull is influenced. Further, garbage collected by adopting the existing solution is easily scatteredly fallen from an opening, and the collection effect is not good. The body of the automatic water surface skimmer is provided with an accommodating cavity running through upper and lower portions, such that a storage member can be placed from the top to the bottom, and it is convenient for a user to disassemble and assemble the storage member.

Abstract: System for launch and recovery of a surface vehicle, comprising a floating cradle structure configured to receive the surface vehicle, the cradle structure being bottomless such that contact between a submersed portion of the surface vehicle and the cradle structure is avoided upon receiving the surface vehicle.

Abstract: The present invention discloses a tracking-type floating solar power generation device. The present invention provides the tracking-type floating solar power generation device, in which a central plate-shaped floating buoyancy central-axis member on which power conversion equipment is mounted is constructed in a barge form facilitating the fabrication of a structure and having secure durability through the continuous assembly of individual containers, a central buoyant part having a vertical stack structure is constructed under the floating buoyancy central-axis member, and outer buoyant parts which are separate from the floating buoyancy central-axis member outside the floating buoyancy central-axis member, which form multiple concentric circles, and on which solar modules are regularly seated are successively connected at constant intervals by maintaining bars and basic bars, thereby completing a floating solar light power plant that forms an independent island structure.

Abstract: A motion-state dependent method for operating a kinetic generator on a marine vessels or platform includes determining a motion state of the marine vessels or platform, and imposing a limit on at least one of charging and discharging of the kinetic generator based upon the motion state to keep the kinetic generator within a safe operating range.

Abstract: A portable, pumpless water ballast system can be constructed of a flexible water-proof membrane molded or formed of welded panels to make a desired shape, such as cube-shaped when filled with water. Along the top side is an opening for filling the container. A water-proof closure is provided in the opening to prevent water leaking out. An air release valve can be installed near the top area of the container's top or side panels. A handle or strap can also be provided on one or more of the adjacent sides of the container. A plastic threaded drain and closure can be provided on one or more sides to allow for emptying of the container or to attach other features like a hose or other accessory.

Abstract: The invention provides a waveguide element (1000) comprising a first face (1001) and a second face (1002) with radiation transmissive material (1005) configured between the first face (1001) and the second face (1002), wherein the radiation transmissive material (1005) is transmissive for UV radiation, wherein the radiation transmissive material (1005) is a matrix material for a phase (1010) of another composition than the radiation transmissive material (1005), wherein the phase (1010) is available in the matrix as regions (1110) with the regions (1110) having mean particle radii (r1) selected from the range of 50-1500 nm and having an average region concentration selected from the range of 1*104-1.5*108/mm3 of the radiation transmissive material (1005).

Abstract: Systems and methods to allow a user to be both towed by and control a personal flotation craft from behind and underneath while engaging in underwater exploration comprising one or more propulsion devices, an optionally foldable tow shaft and one or more directional controllers. Wherein the systems and methods may further comprises one or more remotely controllable speed modulators, controlled by a user from behind and underneath the personal flotation craft, while engaging in underwater exploration.

Abstract: A propeller. The blades of the propeller are characterized by a blade center axis which corresponds to a generator line of a cone to which the blade, or blade thrust surface, conforms. The propeller hub is fixed to the blade at the root, in line with the blade center axis, such that the hub axis and blade center axis lie in the same plane, and the leading edge of the blade is positioned forward (referring to the upstream direction of movement caused by the propeller) of the trailing edge of the blade.

Abstract: A marine propulsion unit of a marine vessel includes a casing provided above a duct to house a steering shaft and a controller configured or programmed to control driving of a propeller, the casing being rotatable by the steering shaft, a power supply wire to supply power to a stator, and a signal wire to transmit a drive signal to the controller. The power supply wire and the signal wire are located outside and along the casing so as to pass in front of the steering shaft along a rotation direction of the steering shaft from a first side to a second side of the casing, the first and second sides being opposite to each other with respect to a forward-rearward direction in a plan view thereof.

Abstract: A jet propelled boat includes a boat body, a hatch, a pair of front end movement restrictors spaced apart from each other in a right-left direction in a vicinity of a front end of the hatch so as to restrict movement of the front end with respect to the deck, a rear end lock provided in a vicinity of a rear end of the hatch so as to restrict upward movement of the rear end, and a pair of rear end movement restrictors provided on both sides of the rear end lock in the right-left direction so as to restrict horizontal movement of the rear end.

Abstract: An objective of the disclosure is to provide a simulation method for a two-stage plunger pressurized common rail fuel system of a marine low-speed engine. The method includes: first setting initial status parameters, such as a control step of a system model, a total time of a calculation process, and structure parameters and pressures of components; and then establishing a mathematical model of a fuel booster unit, a mathematical model of a high-pressure fuel pipe and a mathematical model of a fuel injector based on a MATLAB simulation platform, and connecting input and output parameters of the models to realize data transfer between the models. By considering one-dimensional (1D) spatial fluctuations in the high-pressure fuel pipe, the disclosure establishes a high-precision model of the fuel system, which provides an effective method for designing and calculating detailed pressures in the common rail fuel system.

Abstract: A control device of a marine propulsion device, which has an engine and a propeller and is mounted on a hull. The control device includes a processor, and a non-transitory storage medium having program instructions stored thereon. The execution of the program instructions by the processor causes the control device to acquire a rotation speed of the engine or a rotation speed of the propeller, acquire a torque of the engine, acquire a speed of the hull, and determine whether a ventilation of the engine has occurred based on at least two among the acquired rotation speed, the acquired engine torque, and the acquired hull speed.

Abstract: A marine propulsion unit of a marine vessel includes a casing provided to house the steering shaft and a controller configured or programmed to control driving of a propeller, the casing being rotatable by the steering shaft, a power supply wire to supply power to the stator, and a signal wire to transmit a drive signal to the controller. The power supply wire and the signal wire are located outside and along the casing so as to pass behind the steering shaft from a first side to a second side of the casing, the first and second sides being opposite to each other with respect to a forward-rearward direction in a plan view thereof.

Abstract: A reactor configured to clean ballast water on ships includes a reactor housing having an inlet and an outlet and a reactor tube in the reactor housing providing a fluid connection between the inlet and the outlet. The reactor tube includes an inner wall having a plurality of rounded recesses extending longitudinally from a first end of the reactor tube to a second end of the reactor tube, and the rounded recesses each have a substantially constant cross section from the first end of the reactor tube to the second end of the reactor tube. A radially inwardly projecting ridge extends between each circumferentially adjacent pair of the rounded recesses.

Abstract: Systems, apparatuses, and methods for constructing an airship quickly and cost-effectively are described.

Abstract: The present disclosure provides aerostat display, which utilizes the aerial display by exploiting the visual residue of pointolites rotating around the outer surface of the aerostat on human eyes.

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

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

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

Abstract: A floor structure for an aircraft includes a rail that defines a recess having an opening and a bottom and designed to receive one or more attachment elements, a covering element arranged above a segment of the recess so as to provide a complementary bearing surface above the opening, and a cellular supporting structure having a first end that rests on the bottom of the recess, and a second end supporting the covering element. Thus, the covering element can be sufficiently thin to avoid or limit the formation of steps at the surface of the floor structure.

Abstract: A disclosed method reduces a wave drag on an airfoil traveling at a speed. At least a portion of the airfoil is configured to be selectively moveable between a first position and a second position. The first position is a neutral position, and the second position generates a shock wave near to the leading edge of the airfoil. The method includes the steps of maintaining the airfoil in the first position when the speed is less than a first limit and moving the airfoil to the second position when the speed is greater than a first limit.

Abstract: A ducted-rotor aircraft may include a fuselage and first and second ducts that are coupled to the fuselage at respective first and second locations. The first location may be on a first side of a fuselage of the aircraft and spaced from a nominal yaw axis of the aircraft. The second location may be on an opposed second side of the fuselage and spaced from the nominal yaw axis. Each duct may include a rotor that is disposed in an opening that extends through the duct. Each rotor may include a plurality of blades. Each duct may further include a control vane that is mounted aft of the plurality of blades and that is pivotable about a vane axis that is oriented toward the nominal yaw axis.

Abstract: A leading-edge component for an aircraft includes at least a part of a flow body having a front skin and at least one rib, wherein the front skin includes a top section, a bottom section and a leading edge arranged therebetween, wherein the rib extends from the bottom section to the top section, wherein the rib includes at least one kink separating the rib into a first section and at least one second section, and wherein main extension planes of the first section and the at least one second section enclose an angle of at least 10°.

Abstract: A ducted-rotor aircraft includes a fuselage, one or more ducts, and a spindle that rotatably couples the one or more ducts to the fuselage. Each duct includes a hub that is configured to support a rotor, a plurality of stators that are coupled to the hub, a duct ring that is coupled to the plurality of stators, and a fitting that is coupled to a first stator of the plurality of stators. The fitting has a tubular collar that defines a first aperture that extends through the fitting. The collar is configured to receive a portion of the spindle. The first stator includes a rib that is spaced inward from the fitting and that defines a second aperture that is aligned with the first aperture and that is configured to receive an end of the spindle.

Abstract: A ducted-rotor aircraft includes a fuselage and first and second ducts that are coupled to the fuselage. Each duct includes a duct ring, a rotor having a plurality of blades, a hub that positions the rotor such that the blades define a blade plane of rotation within the duct ring, and a plurality of stators that are coupled to the hub at respective locations aft of the blade plane of rotation. Each of the plurality of stators defines a leading edge that is slanted toward the blade plane of rotation. The leading edges of the stators are slanted to follow a contour defined by the blades. The leading edges may also be slanted to maintain a distance of at least one blade inboard chord length between the leading edges of the stators and respective trailing edges of the blades.

Abstract: A duct for a ducted-rotor aircraft includes a hub, a duct ring, and a plurality of stators that extend outward from the hub. The hub may be configured to support a motor. The duct ring defines a trailing edge. The duct ring is coupled to each of the plurality of stators such that all or substantially all of each of the plurality of stators is located aft of the trailing edge of the duct ring.

Abstract: Methods and systems for adjusting a force feel profile of an inceptor of an aircraft are provided. The force feel profile is based on a baseline value of an operating parameter of the aircraft and defines an amount of resistive force applied to the inceptor as a function of displacement of the inceptor. An embodiment of the method includes receiving data indicative of a current value of the operating parameter. Based on a difference between the current value and the baseline value of the operating parameter, a portion of the force feel profile corresponding to a range of displacement values is shifted to adjust an amount of resistive force defined by the portion of the force feel profile for the range of displacement values.

Abstract: A device includes a lever associated with a body carrying a plate that is connected to the body by a pivot connection for pivoting about a first axis, the lever being connected to the plate by a pivot connection for pivoting about a second axis, a first transmission shaft and a first connection mechanism for connecting the lever to the first transmission shaft, a second transmission shaft and a second connection mechanism for connecting the control lever to the second shaft. The first shaft and the first connection mechanism are connected together by a pivot connection for pivoting about a fifth axis that is inclined relative to the first axis and to the third axis, and the second shaft and the second connection mechanism are connected together by a pivot connection for pivoting about a sixth axis that is inclined relative to the second axis and to the fourth axis.

Abstract: Methods and systems for operating actuator control electronics are described. In an example, a system can include a first lane and a second lane configured to be in communication with each other. The first lane can receive first data associated with a first pattern and send the first pattern to the second lane. The second lane can receive second data associated with a second pattern and send the second pattern to the first lane. The first and second lanes can each compare the first pattern with the second pattern. Based on the comparison, the first lane can select first input data and the second lane can select second input data. The first lane can generate a first actuator command using the first input data. The second lane can generate a second actuator command using the second input data. The first and second actuator commands can be bit-for-bit identical.

Abstract: A winglet system for a wing of an aircraft is provided. The winglet system comprises an attachment end for attachment to a main wing of the aircraft, an upper winglet and a lower winglet. The upper and lower winglets are staggered and also overlap one another along the chord of the attachment end. A spanwise profile of the lower winglet has a midpoint where a slope of the spanwise profile at a point outboard of the midpoint is inclined more upwardly than a slope of the spanwise profile at the midpoint. The configuration of the winglet system may provide benefits such as a reduced bending moment and reduced negative interference between the winglets while also managing ground clearance.

Abstract: A system and method for protecting a rotorcraft from entering a vortex ring state, the method including monitoring a vertical speed of a rotorcraft, comparing the vertical speed to a vertical speed safety threshold, and performing vortex ring state (VRS) avoidance in response to the vertical speed exceeding the vertical speed safety threshold. The performing the VRS avoidance includes determining a power margin available from one or more engines of the rotorcraft, limiting the vertical speed of the rotorcraft in response to the power margin exceeding a threshold, and increasing a forward airspeed of the rotorcraft in response to the power margin not exceeding the threshold.

Abstract: According to an aspect, a clevis assembly includes a shackle having two ends, each end respectively including an aperture, a structure connecting the apertures and housing a bearing, and a shearing device that includes a frangible point and is in operable communication with the bearing, where the shearing device is housed in a hollow portion of the structure.

Abstract: A ducted-rotor aircraft includes a fuselage, first and second ducts, and a spindle that is coupled to the fuselage. Each duct includes a rotor having a plurality of blades. The first and second ducts are coupled to opposed ends of the spindle. The spindle is rotatably coupled to the fuselage with first and second bearings. The first bearing is configured to react to radial loads and the second bearing is configured to react to both radial and axial loads. The spindle includes a shaft, first and second fittings secured to opposed ends of the shaft, and first and second attachment interfaces that are attachable to the first and second ducts. The attachment interfaces may be integral with the fittings. Alternatively, the fittings may be configured to be secured to the attachment interfaces with fasteners.

Abstract: An aircraft includes a fuselage module and at least two vertical lift rotor modules supporting at least four rotor assemblies. Each rotor assembly is supported by a rotor boom having at least one boom free end and a boom mounting portion. Each rotor assembly has at least one vertical lift rotor mounted on the boom free end. Each boom mounting portion is removably couplable to the fuselage module. The vertical lift rotor modules are configured such that when coupled to the fuselage module, a pair of the rotor assemblies are located on each of laterally opposite sides of the fuselage module, and the rotor assemblies of each pair are respectively located forward of and aft of a wing center portion. A pair of wings are configured to be removably couplable to the wing center portion. The aircraft includes a forward thrust module removably couplable to the fuselage body.

Abstract: A system for aircraft collision avoidance includes a first aircraft, the first aircraft configured to detecting at least a projected flight path of at least a second aircraft, determine, as a function of the at least a projected flight path, that the first aircraft is on a collision course with the at least a second aircraft, select a collision avoidance maneuver, the collision avoidance maneuver including at least a flight path for the first aircraft and at least a flight path for the at least a second aircraft, and transmit the collision avoidance maneuver to the at least a second aircraft.

Abstract: Unauthorized operation of a UAV may present privacy or security risks. A software-defined radio (SDR) or other receiver can be used to monitor a specified range of frequencies to provide detection of wireless communication signals suspected of relating to UAV operation. A protocol detector corresponding to a trained classifier can be applied to data packets demodulated by the SDR. A transmitter can then be triggered to provide warnings by injecting warning data into a video channel in response to the detected protocol. Control of the UAV can be established by transmitting simulated control commands that overwhelm the signals received from the UAVs normal remote control. If transmission of warnings or simulated control signals fail to suppress unwanted UAV operation, other actions can be triggered such as jamming or dispatch of an interceptor such as a surveillance UAV.

Abstract: An unmanned aerial vehicle (UAV) according to an embodiment of a present invention may include a drive motor that rotates a propeller in a clockwise or counterclockwise direction, and a servo motor that tilts the propeller, so that it may fly in a posture for calibration of sensors. An unmanned aerial vehicle (UAV) according to an embodiment of the present invention may be linked to an Artificial Intelligence module, a robot, a device related to a 5G service, and the like.

Abstract: A diaphragm pump includes a pump body mechanism, a one-way valve mechanism, a diaphragm mechanism, a motor mechanism, and an eccentric mechanism. The one-way valve mechanism includes a one-way valve and a valve cover configured to mount the one-way valve at the pump body mechanism. The diaphragm mechanism includes a pump cover mounted at the pump body mechanism and a diaphragm connected to the pump cover. The pump cover is configured to cover the diaphragm and the valve cover. The one-way valve mechanism, the diaphragm mechanism, the motor mechanism, and the eccentric mechanism are mounted at the pump body mechanism.

Abstract: An aircraft hoist system includes hoist equipment arranged in an aircraft, the hoist equipment including a motor, a cable, and a hook portion. The aircraft hoist system also includes at least one sensor configured to obtain measurements and a processor configured to analyze the measurements from the at least one sensor. The aircraft hoist system also includes the processor configured to determine motor control signals to control the motor based on an analysis of the measurements from the at least one sensor to reduce sway and/or oscillations of the cable while lifting a load. The aircraft hoist system also includes the processor configured to control the motor to lift the load with the cable based on the determined motor control signals.