Abstract: A leaning vehicle including a vehicle body, at least one front wheel, at least one rear wheel, a leaning device that causes the vehicle body, the at least one front wheel and the at least one rear wheel to lean leftward or rightward at the left-turn or right-turn of the leaning vehicle, a steering handle rotatable counter-clockwise or clockwise to turn the at least one front wheel left or right, a lean actuator supplying power to the leaning device, and a control unit that controls the lean actuator in accordance with an amount of rotation of the steering handle detected by a steering-handle rotation sensor. The control unit is configured to, when the steering handle is rotated within a particular rotation range, control the lean actuator to restrain the vehicle body, the at least one front wheel and the at least one rear wheel from leaning.

Abstract: A lever system using a linkage assembly creates linear movement from a rotational movement of a lever. The lever system may be arranged as a grip assembly to activate a braking system of a vehicle. The linkage assembly may include a slide linkage, a bearing linkage, and a pivot linkage such that the lever may cause an end of the bearing linkage and an end of the pivot linkage to move toward the slide linkage, which causes the slide linkage to move in a linear direction. The grip assembly may have a lever that is pivotally connected with a housing of the grip assembly at a predetermined distance and with a contact region to prevent rotational movement in one direction while allowing rotational movement in the opposite direction. Further, the grip assembly may include a bearing linkage that is pivotally connected to the lever.

Abstract: A braking system includes a vehicle having a front brake and a rear brake. The system includes a moveable structure connected to a rear brake. The rear brake may be a hydraulic brake. When the rear brake is actuated, the moveable structure moves. The movement of the structure pressurizes hydraulic fluid in a tube which actuates a front hydraulic brake.

Abstract: A pedal powered bag transport cart/cycle is a personal riding cart/cycle adapted to transport a rider and a bag. The cart/cycle is generally symmetrical about a longitudinal plane and includes a frame with a seat, a front wheel and steering components, a rear wheel, an inclined bag support, a pedal subassembly, and in some embodiments a motor assist subassembly and controls.

Abstract: A multi-sprocket arrangement for a rear wheel hub of a bicycle may have improved gearshift characteristics, reduced vibrations during skewed running, and improved wear characteristics. The multi-sprocket arrangement includes a multiplicity of sprockets of different diameters, wherein at least one of the sprockets has a multiplicity of teeth. Also on the circumference of said sprocket, as viewed in a circumferential direction, at least one sequence of teeth is provided in which, with regard to their material thickness, a thin tooth is followed by a thick tooth which is followed in turn by another thin tooth.

Abstract: The disclosure describes an electromechanical rear derailleur for coaxial mounting on a rear wheel axis. The rear derailleur has a base member, a pivot mechanism, a movable member having a chain guiding arrangement, and an electromechanical drive for driving the pivot mechanism. The pivot mechanism connects the base member to the movable member. The chain guiding arrangement is connected to the movable member for rotation about an axis of rotation. The base member comprises a first connection end, which can be mounted coaxially with the rear wheel axis, and a second connection end for coupling with the pivot mechanism.

Abstract: A barrier accessory device for a watercraft includes: an accessory connection base configured for having at least one accessory removably connected thereto; a first rail connector connected to the accessory connection base at a first end portion thereof, the first rail connector having a slot-engaging member configured to be inserted into a slot defined in one of an upper rail and a lower rail of a barrier structure of the watercraft; and a second rail connector connected to the accessory connection base at a second end portion thereof opposite the first end portion, the second rail connector having a locking assembly configured to be selectively locked onto an other one of the upper rail and the lower rail.

Abstract: A mooring ball system comprising: a mooring ball; a collar attached to the top of the mooring ball; an extendible, retractable, and lockable mast attached to the collar, and extending from the top of the mooring ball; a hook attached near or at the top of the mast; a chain attached to the mooring ball; a mooring line attached to the chain; a loop located at one end of the mooring line; and where the loop is configured to removeably attach to the hook, and where the loop is further configured to be removed from the hook and attached to a watercraft. A mooring apparatus comprising: a collar configured to attach to the top of a mooring ball; an extendible, retractable, and lockable mast configured to attach to the collar, and configured to extend from the top of the mooring ball; and a hook attached near or at the top of the mast.

Abstract: A system for restriction of hawser movement in a tandem mooring and loading system is provided comprising a first floating structure being spread moored, a second floating structure, and a tandem mooring arrangement between the first and second floating structure. The tandem mooring arrangement comprises at least one hawser connected in a first end to a hawser connection arrangement on the first floating structure, and in a second end connected to a hawser connection point on the second floating structure and a loading arrangement, wherein the system further comprises a hawser guide arrangement.

Abstract: A method of unloading cargo at sea from a cargo vessel to a cargo barge, comprising the steps of providing a catamaran vessel having a pair of spaced apart catamaran hulls and a pair of spaced apart arch shaped frames, each frame attached to each hull at a frame lower end portion; positioning the cargo vessel in between the hulls and under the top portion of the frames; placing one or more cargo barges next to one or both of the hulls, wherein the hull is in between the cargo vessel and the cargo barge; and unloading cargo from the cargo vessel to the cargo barge wherein the cargo travels from the cargo vessel, over the catamaran hull to the cargo barge.

Abstract: A watercraft mounting system that embodies a moving mounting platform and a protective hull cavity which provides protection, prevents damage and improves storage of data collection systems.

Abstract: A marine propulsion device has a powerhead, a driveshaft powered by the powerhead, a lower unit, and a propeller shaft supported in the lower unit and in torque transmitting relationship with the driveshaft. The marine propulsion device also has a steering column through which the driveshaft extends and to which the lower unit is coupled. The steering column is configured to rotate the lower unit with respect to the powerhead. There is a steering housing through which the steering column extends, the steering housing being stationary with respect to the powerhead. A flexible conduit, for example a wiring harness, extends through an aperture in the steering housing and through an aperture in the steering column. The flexible conduit has slack between the steering housing and the steering column.

Abstract: A small watercraft system includes: a watercraft body; a watercraft body manipulation member through which a watercraft body manipulation command is input by an operator; a drive source that allows the watercraft body to plane; a steering device that allows the watercraft body to be steered; and a control device that controls the drive source and the steering device to operate the watercraft body. The control device determines whether a mode switching condition is satisfied, the mode switching condition including an operator's absence condition that the operator is absent from the watercraft body. Upon determining that the mode switching condition is satisfied, the control device executes an operator-absent manipulation mode in which the control device moves the watercraft body by controlling the drive source and the steering device based on an operator-absent manipulation command independent of the watercraft body manipulation command.

Abstract: The present disclosure provides a swimming auxiliary equipment, including an auxiliary equipment main body, a strap, a connecting belt and two arm jackets, wherein two sides of the auxiliary equipment main body are tied to the waist of a swimmer through the strap, and the arm jackets are connected to the auxiliary equipment main body through the connecting belt; the auxiliary equipment main body includes a first air bag, a cavity is arranged inside a waterproof layer, the first air bag is arranged in the cavity, and a pressure sensor is arranged on an inner wall of the auxiliary equipment main body; and the auxiliary equipment main body includes an expansion bin arranged in the cavity and a net structure with a plurality of connected layers, a priming device is arranged on the net structure, and the priming device is arranged in the cavity and connected to the pressure sensor.

Abstract: A watercraft and associated pedal drive system are provided. Method of operating the pedal drive are also provided. The pedal drive system allows for unassisted manual pedaling to provide thrust to the watercraft. The pedal drive system also provides on demand pedal assistance of varying levels via an assist drive train having an electric motor to supplement the manual pedal force input provided by a user at the pedals of pedal drive system.

Abstract: A marine drive is for propelling a marine vessel in a body of water. The marine drive has a supporting frame configured to support the marine drive with respect to the marine vessel, an extension leg depending on the supporting frame, a motor housing depending on the extension leg, the motor housing for containing an electric motor, and a vibration isolating joint which couples the extension leg to the supporting frame. The vibration isolating joint having an isolating connector assembly including an elastomeric member which is clamped between the extension leg and the supporting frame and configured to limit transfer of vibrations from the extension leg to the supporting frame, and a compression limiter which prevents over clamping of the elastomeric member during assembly of the extension leg and the motor housing.

Abstract: A trim and tilt device includes: a cylinder; a piston; a rod; and a rod guide. The rod includes a first end to which the piston is fixed, and the piston includes an insertion hole to which the first end of the rod is inserted. Over an entire periphery of the rod guide, a lower end of an outer peripheral surface of the rod guide that is in contact with the inner peripheral surface of the cylinder is located closer to a second end of the rod than a lower end of a first inner peripheral surface of the rod guide where the outer peripheral surface of the rod is slidable. An upper end of an outer peripheral surface of the piston is located closer to the second end of the rod than an upper end of the insertion hole.

Abstract: A power storage system for a marine vehicle is provided. The power storage system includes marine battery systems configured to provide energy to a marine vehicle load. Each marine battery system includes a battery and a three-position contactor configured to operate the marine battery system in one of a connected state, a disconnected state, or a bypass state. The power storage system further includes a controller coupled to each of the marine battery systems. The controller is configured to retrieve a preferred fault action for the marine battery systems, and in response to detection of a fault condition in the marine vehicle, control at least one three-position contactor of the marine battery systems according to the preferred fault action. The preferred fault action includes operating the marine battery system in the disconnected state or operating the marine battery system in the bypass state.

Abstract: A marine propulsion system includes marine propulsion devices each including a propeller shaft, an engine, an electric motor, a power transmission to transmit mechanical power to the propeller shaft from at least one of the engine and the electric motor, an electric circuit connected to the electric motor, and a controller to control the engine. The controllers in the marine propulsion devices are communicable with each other when in a communicable state. When the controller in each of the marine propulsion devices is in the communicable state, but the controller of one of the marine propulsion devices is incommunicable with any other controller of the marine propulsion devices, the incommunicable controller limits an output of the engine controlled by the incommunicable controller.

Abstract: A ship body control device is provided, which includes a control lever having a neutral position, and processing circuitry. When the control lever is moved during an automatic cruise, the processing circuitry executes a deceleration control from a speed of a ship body during the automatic cruise, and when the position of the control lever is in agreement with a position for changing to a manual cruise, the processing circuitry changes the automatic cruise to the manual cruise at a rotating speed of an engine according to the position for changing to the manual cruise.

Abstract: A hull control device is provided, which includes an error distance calculating module, an approaching speed calculating module and a command value setting module. The error distance calculating module calculates an error distance between a target position of a fixed-point hold and a ship position. The approaching speed calculating module calculates an approaching speed of a ship to the target position. The command value setting module sets a throttle command value according to a combination of the error distance and the approaching speed.

Abstract: A drive system for a ship, including at least two propulsion units, each propulsion unit having a propeller and a drive engine with an above-water transmission connected downstream for driving the propeller. Each drive engine can be connected to and disconnected from the associated above-water transmission with a clutch and between the above-water transmissions, a switchable drive train is provided by which in one switching state, the above-water transmissions can be coupled and driven jointly and in another switching state, they can be decoupled from each other.

Abstract: A method for operating a propulsion device having a propulsor with a propeller, the propulsion device having a base coupled to a marine vessel and being configured to propel the marine vessel in water. The method includes moving the propulsor from a deployed position towards a stowed position, where the propulsor is closer to the marine vessel in the stowed position than in the deployed position, and where the propulsor is configured to propel the marine vessel in the deployed position. The method further includes rotating the propeller so as to fit between sides of the base coupled to the marine vessel when the propulsor is in the stowed position.

Abstract: A device for sensing a physical parameter includes a sensor element configured for measuring the physical parameter and for outputting a corresponding measured signal, wherein the measured signal is influenceable by a sensor drift of the sensor element. The device includes a corrector for correcting the measured signal output by the sensor element to obtain a corrected signal, wherein the corrector is configured for evaluating the measured signal to determine a drift effect of the sensor drift on the measured signal and for correcting the measured signal so as to at least partially compensate for the drift effect. The device includes a signal output configured for outputting the corrected signal.

Abstract: An aircraft windshield wiper system includes a wiper arm, a wiper blade coupled to a first end of the wiper arm, and an output shaft coupled to a second end of the wiper arm. The wiper blade includes a fluid dispensing system including nozzles, a fluid control unit, fluid lines, fluid source, and a user interface. The wiper blade with the fluid dispensing system is configured to dispense a variety of fluids directly from the wiper blade onto the windshield of an aircraft.

Abstract: A windshield wiper system for use on an aircraft includes a controller and a wiper assembly including a wiper arm, a wiper blade, and a moving block. Further, the windshield wiper system includes a rail assembly including a rail assembly rack, a plurality of electromagnets, and an electrical interface. The electrical interface and the plurality of electromagnets induce a force on the moving block of the wiper assembly, causing the wiper assembly to sweep across the windshield of the aircraft. The controller is coupled to the rail assembly and the controller is configured to direct the motion of the wiper assembly through command signals to the rail assembly.

Abstract: A floor panel for installation in an aircraft includes a plurality of thermoplastic C-shaped stringers, a consolidated thermoplastic deltoid filler, a thermoplastic upper facing sheet, and a thermoplastic lower facing sheet. The stringers are disposed in a parallel arrangement with one another. The deltoid filler is disposed within a longitudinally-extending notch defined by a pair of adjacent stringers. The upper facing sheet covers an upper surface of the stringers and the deltoid filler. The lower facing sheet covers a lower surface of the stringers and the deltoid filler. The stringers, the deltoid filler, and the upper and lower facing sheets are integrally consolidated forming a unitary construction.

Abstract: A blanket for insulating an aircraft structure comprises an insulating portion, comprising a first edge and a second edge, perpendicular to the first edge. The blanket also comprises a tab portion, extending from the insulating portion, and a formable coupler, attached to the insulating portion. The tab portion is thinner than the insulating portion. The insulating portion fully overlaps the formable coupler. The formable coupler is parallel to the second edge of the insulating portion and is perpendicular to the first edge of the insulating portion.

Abstract: A propeller safety device is provided. The propeller safety device is configured to insert a moving part of a propeller into a fixed part during a crash of an air mobility to allow a reduction in the total length of the propeller, thereby preventing the propeller from hitting the ground. Accordingly, a secondary accident due to fragments formed when the rotating propeller hits the ground is prevented.

Abstract: A system and method for detecting fixed pitch operation of a variable pitch propeller of an engine are provided. A command signal for maintaining a rotational speed of the propeller at a reference speed is output. An actual value of at least one of the rotational speed and a blade angle of the propeller is obtained. From the actual value, it is assessed whether an expected change in the at least one of the rotational speed and the blade angle of the propeller has occurred in response to the command signal. Responsive to determining that the expected change in the at least one of the rotational speed and the blade angle of the propeller has not occurred in response to the command signal, operation of the propeller at fixed pitch is detected and an alert output accordingly.

Abstract: A system of an electric aircraft with pitch control using an elevator is presented. In some embodiments, the electric aircraft may include an elevator configured to deflect. In some embodiments, the electric aircraft may further include a lift lever configured to generate a lift command upon activation by a pilot. In some embodiments, the electric aircraft may further include a flight controller communicatively connected with the lift lever and the elevator, wherein the flight controller is configured to receive the lift command from the lift lever and adjust the elevator as a function of the lift command.

Abstract: The invention relates to a force application device for a control stick of an aircraft, said control stick comprising a control lever that is connected to at least one motor comprising a drive shaft that can be rotated about an axis, the force application device comprising: a first pin connected to the shaft, a housing, an electromagnet, a movable actuator comprising a magnetic material, a coupling device comprising an input gear connected to the housing and an output gear comprising a second pin, and means for clamping the first pin and the second pin which comprise a first tooth and a second tooth, said device having an operating configuration in which the electromagnet is active and the output gear is positioned at a distance from the input gear, and a blocking configuration in which the electromagnet is inactive and the gears are meshed.

Abstract: A system and method for controlling an actuator for a control surface of an aircraft includes a processing unit configured for acquiring a set of N values of the same parameter, N being equal to 2×p or to 2×p+1, p being an integer greater than or equal to 2, and determining a voted value of the parameter by a voter (15) with N inputs. The voter with N inputs includes a module for determining two intermediate values from among the values of a subset of 2×p values of the set of N values of the parameter, this module including at least p+1 voters with 2×p?1 inputs, receiving as input distinct subsets of 2×p?1 inputs of the subset of 2×p inputs, two sub-modules for determining a maximum value and a minimum value, respectively, each receiving as input the outputs of the various voters with 2×p?1 inputs and delivering as output the two intermediate values.

Abstract: An actuator arrangement for a fixed leading edge member of an aircraft wing. The fixed leading edge member has an inner cavity defined by the outer skin and ribs. The actuator arrangement comprises at least one geared rotary actuator which moves relative to the other parts along a circular arc section during extending and retracting of the high-lift device between a fully retracted position and a fully extended position. In the fully retracted position, the actuator is predominantly accommodated within the inner cavity and in the extended position the actuator is predominantly positioned outside the inner cavity, preferably protruding through a D-nose cut-out.

Abstract: This invention is an apparatus for vortex generation by combining the function of means for vortex generation with the functions of the leading-edge aerodynamic surface, the airfoil, and/or the trailing-edge aerodynamic surface.

Abstract: An aircraft landing gear support (1) including: a support member (such as a landing gear rib (2)) and a plurality of pintle supports (5, 7, 8) (typically in the form of lugs) which form a pintle support arrangement for holding a pintle on which a landing gear assembly may be rotatably supported. The lugs are removably attached to the gear rib.

Abstract: Disclosed are various embodiments for reducing or eliminating the nose-down pitching moment during water landings of amphibious aircraft when the landing gear is in the down position. Shielding struts forward of the wheels generate hydrodynamic lift and reduce hydrodynamic drag in order to alter the pitching moment about the aircraft center of mass.

Abstract: A rotor for a hover-capable aircraft includes an attenuating device to attenuate the transmission of vibrations from a mast to the aircraft. The attenuating device includes a first mass free to oscillate parallel to a hub rotation axis with respect to a casing of the attenuating device and elastically connected to the casing. The attenuating device further includes a second mass free to oscillate parallel to the hub rotation axis, connection means adapted to make the first and second masses integrally movable along the hub rotation axis when the angular speed of the mast assumes a first value, and actuator means activatable to decouple the first and second masses when the angular speed of the mast assumes a second value, different from the first value.

Abstract: The present invention provides a power device generating greater propelling force and finds that traditional power devices do not include all propelling forces based on the fundamental core propelling force source problem. External pressure is guided to the traditional power devices since the inner speed is higher the outer speed, power consumption for overcoming fluid resistance is high, and mutual contradiction results are obtained. The unique difference between the present invention and general common sense lies in opposite fluid pressure directions; inner fluid channels and outer fluid channels with higher flow speeds are formed to generate pressure differences which guides the fluid pressure to the outside and serve as propelling force, thus the present invention creatively finds three propelling force sources, two lifting force or propelling force sources of helicopters or airplanes driven by propellers and two propelling force sources for sufficient burning of fuel in combustion chambers of engines.

Abstract: A helicopter includes annular rotors surrounding a fuselage. Rotor blades extend radially outwardly from each annular rotor. One or more motors is provided. Each motor rotates a roller, which drives each annular rotor by traction. In an embodiment with two rotors, one rotor rotates in one direction and the other rotor rotates in the opposite direction. A swash device with a grooved outer cylindrical surface engages the free end of a crank arm of each rotor blade to provide collective and cyclic pitch control. Actuators, which may be electromechanical or hydraulic, control positioning and movement of the swash device. Batteries, an electric generator and/or a hydrogen fuel cell may supply electric power.

Abstract: An electrically distributed yaw control system for a helicopter having a tailboom and a power system includes one or more tail rotors including a motor rotatably coupled to the tailboom and a power distribution unit. The power distribution unit includes a power management monitoring module configured to monitor one or more flight parameters of the helicopter and a power management command module configured to allocate power between the power system and the one or more tail rotor motors based on the one or more flight parameters of the helicopter.

Abstract: A parking tail rotor for a rotary wing aircraft stops rotating at a high forward aircraft speed when aircraft control surfaces have adequate control authority to balance main rotor torque without the rotating tail rotor. When stopped, the blades of the parking tail rotor move due to the force of the relative wind to a parked position in which the span of the blades extend in the aft direction, reducing air resistance to the forward motion of the aircraft.

Abstract: The present invention provides an aircraft design which incorporates a modular design including the use of one or more multi-motor assemblies where the motors are in series within the multi-motor assembly. Still further, the multi-motor assemblies may be configured to include modular motor assemblies or modular sections. Ultimately, the present invention provides an aircraft with the ability to easily assemble or expand the multi-motor assemblies and, in doing so, modify the characteristics of the aircraft. The modularity also enhances the ability to maintain the aircraft by enabling motors or the units housing each motor to easily be replaced.

Abstract: Duct stringers for aircraft wing boxes. The duct stringer comprises a base, a pair of sidewalls projecting from the base in a spaced-apart relationship, and a cap wall that extends between and interconnects the pair of sidewalls, with the cap wall being positioned spaced apart from the base by the pair of sidewalls. The duct stringer further comprises an ovaloid vent formed in the cap wall. The ovaloid vent comprises a perimeter that circumscribes an aperture and that defines a closed shape. The perimeter comprises a pair of curved end regions opposed to one another and that each arc at least substantially through 180 degrees. Each curved end region comprises a non-uniform radius of curvature.

Abstract: A two degrees of freedom actuator for example for multi-bladed rotor of an aircraft with at least two blades that are driven in rotation about a main rotation axis by primary actuator, and a secondary actuator that is arranged to rotate each of said blades about the respective blades' longitudinal axis, with a synchronization means that is operatively arranged for driving the secondary actuator based on an azimuth of the rotor about the main axis for obtaining a determined cyclic pitch of a given amplitude for each blade depending on the azimuth of the rotor.

Abstract: A method for enhancing movement or autonomy, including movement or flight of vehicles or flight vehicles in communication and or GPS degraded and or denied and or non-optimal environments is presented, where 3D area maps and or area maps may be employed, and 3D area maps and or area maps employed may include embedded position, location or GPS date, where the location or GPS data may be used in the present invention to determine vehicle location through image recognition, and using the GPS coordinates or location from the 3D area map of the image recognized, or measuring distance to other know aspects of a 3D area map in the real world, and context or system level information may also be used to estimate obstacle shapes and optimal routes in a potential route of travel or for understanding an area.

Abstract: An enclosure for a UAS includes a housing having a base and a plurality of sidewalls coupled to the base, a motive apparatus coupled to the housing, a platform coupled to the motive apparatus, and a plurality of lids pivotably coupled to the sidewalls and the platform. The platform and the plurality of lids move collectively under control of the motive apparatus (e.g., a linear actuator). Driving the motive apparatus in a first direction causes the platform to raise from a stowed position toward a deployed position and causes each of the plurality of lids to pivot from a closed position toward an open position. Conversely, driving the motive apparatus in a second direction opposite the first direction causes the platform to lower from the deployed position toward the stowed position and causes each of the plurality of lids to pivot from the open position toward the closed position.

Abstract: An unmanned aerial vehicle (UAV) has an air-cooled fuel cell, an air channel comprising a forward facing opening for receiving ram air and connected to the air-cooled fuel cell, and a passive ram air filtration system (PRAFS) configured to filter particulate matter from ram air received into the air channel via the opening.

Abstract: A movable flow body device for an aircraft including an elongated flow body having a main extension axis, a first mechanical interface in a first position along the main extension axis, a second mechanical interface in a second position and a third mechanical interface in a third position. The first mechanical interface may be a master interface arranged in a central region, while the second and third mechanical interfaces are slave interfaces. Preferably, in the outboard position, a link plate between a support lever and a support rib of the flow body is inverted compared to the further inboard mechanical interface, which allows for supporting slimmer and longer flow bodies in the outboard region and providing a rigging hinge line through the whole flow body.

Abstract: An aerodynamic device includes a main aerodynamic body having a leading edge and a trailing edge, a flight control surface coupled to the main aerodynamic body near the trailing edge of the main aerodynamic body, and a rotating body coupled to the flight control surface. The rotating body is rotatable relative to the flight control surface between a stowed position and a deployed position to define a gap. The rotating body is rotated toward the main aerodynamic body while in the stowed position to close the gap. The rotating body is rotated away from the main aerodynamic body while in the deployed position to widen the gap. The gap adjusts an airflow flowing between the main aerodynamic body and the flight control surface.