Abstract: A torque sensor for electrically assisting a vehicle with pedals includes a housing, a first gear, an actuator, and a control circuit. The housing defines a receiving chamber and is configured to be coupled to a drive member. The first gear is rotatably mounted in the receiving chamber. The actuator is received in the receiving chamber and is driven by the first gear. The control circuit including a resistor is received in the receiving chamber and the actuator slides along the resistor as a rider applies force to the pedals, thus for adjusting a resistance value of the control circuit, to allow the control circuit to output a signal which governs the assisting power. The disclosure also includes an electric bicycle using the torque sensor.

Abstract: An engine includes a first cylinder communicating with a first intake port and a first exhaust port, and an exhaust assembly coupled to the engine and including a first exhaust manifold coupled to the first exhaust port. The first exhaust manifold is angled relative to the first exhaust port.

Abstract: A bicycle sprocket comprises a sprocket body and a chain engagement structure. The chain engagement structure includes a plurality of sprocket teeth. The plurality of sprocket teeth include at least one first tooth and at least one second tooth. The at least one first tooth has a first tooth top extending non-parallel to a sprocket-plane perpendicular to a rotational center axis when viewed from a radial direction of the bicycle sprocket. The at least one first tooth has a first axial chain-engagement width that is larger than an inner link space defined between a pair of inner link plates of a bicycle chain and smaller than an outer link space defined between a pair of outer link plates of the bicycle chain. The at least one second tooth has a second axial chain-engagement width that is smaller than the inner link space.

Abstract: A plurality of sprockets which are coaxial with respect to a sprocket rotation axis, are arranged with axial spacing from each other and have different numbers of teeth which are constructed for positive-locking engagement with a bicycle chain. The pinion arrangement has a gear range quotient which is formed by division of the number of teeth of the sprocket having the largest diameter by the number of teeth of the sprocket having the smallest diameter, and has a packing density quotient which is formed by division of the number of sprockets in the sprocket arrangement by the axial spacing measured in millimeters of the axially outermost pinions from each other. The pinion arrangement may have a gear range packing coefficient, formed from the product of the gear range quotient and the packing density quotient, which is greater than 1.25.

Abstract: The invention is a gear shift device for bicycles, comprising: gear shift control components (A1) suited to transmit codified and/or non-codified signals; actuator components (A3.1, A3.2) suited to be applied to the derailleurs (B4.1, B4.2) and suited to receive said signals and at least one management control unit (A2) of said signals. The device comprises a piece of equipment suited to generate electric energy for powering one or more of said control components (A1) and/or said unit (A2) and/or said actuators (A3.1, A3.2) and/or for charging/recharging one or more possible batteries.

Abstract: A bicycle drive unit is basically provided with an input rotational shaft, an output part, a transmission mechanism, an assist motor and a switching mechanism. The transmission mechanism has at least two shift stages, and is configured to change a speed of a rotational input that is input from the input rotational shaft and output this rotational input to the output part. The assist motor is coupled to a power transmission path from the input rotational shaft to the output part, and is driven according to a manual drive force. The switching mechanism is configured to switch a gear changing state of the transmission mechanism by using a rotational force of the assist motor.

Abstract: A motorcycle transmission includes a swingarm which extends from one hinging end to a motorcycle chassis, defining an oscillation axis, at one connection end to a wheel, a homokinetic joint arranged on the side of the hinging end, and a geared coupling positioned on the side of the connection end. The homokinetic joint kinematically reciprocally connects a first end of an input shaft, connected to a power take-off, and a second end of an output shaft mechanically connected to the geared coupling. The geared coupling transmits motion to the wheel. The homokinetic joint performs an instantaneously constant transmission ratio between the first and the second end. The homokinetic joint is offset to the hinging end of the swingarm, in a vertical direction perpendicular to the support surface of the wheel and permits oscillation of the output shaft between a stroke start and a stroke end, parallel to the oscillation axis.

Abstract: A bicycle transmission control apparatus is basically provided with a controller that is configured to control a gear ratio of a transmission based on seat height information of a bicycle seat relative to a bicycle frame, or change a parameter for shifting the transmission based on the seat height information of the bicycle seat relative to the bicycle frame.

Abstract: A snow vehicle suspension is provided for a snow vehicle. The suspension includes a motorcycle frame, and a rear suspension system pivotally coupled with the motorcycle frame, where the rear suspension system supports an endless track. The suspension also includes a suspension strut pivotally coupled at a first end with the motorcycle frame and at a second end pivotally coupled with the rear suspension system, and at least one shock absorber disposed within the endless track.

Abstract: A three stage watercraft for operation in the water as a traditional boat at low speeds in stage one, for operation on the water's surface at mid-range speeds at stage two, and for traveling in ground effect at higher range speeds is disclosed. The three stage craft includes a hydro-wing 12, either at least a single hydrofoil 13 or gyration rotor 14 to aid with lift from stage one to stage two, and a pair of outboard floats or hydro-floats 16a, 16b supported by the hydro-wing 12, which are also designed to aid with lift from stage one to stage two.

Abstract: The invention relates to a fairlead for guiding an anchoring element, allowing the anchoring of a unit, such as a floating unit, to an anchoring point, and in particular being applicable to permanent anchoring devices of the submerged fairlead type with an integrated chain stopper, in fields such as the marine, offshore, and renewable marine energy industries. The fairlead comprises guide means 1 to 4 able to guide the translation of the anchoring element between the unit and the anchoring point, and blocking means 5 able to block the translation of the anchoring element in the guide means 1 to 4. The blocking means 5 are mounted on the guide means 1 to 4 at least partially freely rotating around an axis parallel to the longitudinal axis of the anchoring element when the latter is guided in the guide means 1 to 4.

Abstract: A cable-protecting device is used on a cable of a marine survey system to oppose cable bending and/or to limit a bending radius of the cable. The cable-protecting device has a functional body made of at least two portions configured to be clamped together to surround the cable, a gripping system configured to oppose the functional body sliding along the cable, and a closing system configured enable the at least two portions to engage fast and remain clamped.

Abstract: A liquefied gas tank installed in a surrounding structural body includes: a tank main body in which a liquefied gas is storable, the tank main body including a plurality of planar portions and corner portions between the planar portions, the corner portions having less rigidity than that of the planar portions; a bottom supporting body that supports the tank main body from below the tank main body; and a plurality of side supporting bodies that support the tank main body from side of the tank main body. The tank main body is configured to stand by itself by being supported by the bottom supporting body when the tank main body stores no cargo, and be supported by the bottom supporting body and the side supporting bodies when the liquefied gas is stored in the tank main body.

Abstract: An offshore loading system operable to load a substance between a first structure and a second structure separate from the first structure, the second structure including a manifold, includes a loading arm having a process pipe to carry the substance during a process of loading the substance by the loading arm, the process pipe including a free end, the loading arm coupled to the first structure. A control unit is coupled to the loading arm and operable to direct the free end of the loading arm, and a first acceleration sensor electronically coupled to the control unit. The first acceleration sensor is operable to detect relative movement of the first structure with respect to the second structure.

Abstract: A ride height adjustable oil damped air shock boat seat pedestal with selectively lockable swivel capability is shown, which includes a locking pin extending below the seat and moving up and down with the seat as permitted and controlled by the air shock. The locking pin being received by a structure, which limits rotation of the seat.

Abstract: The present invention is a stand up paddle board with left and right oars attached to left and right transmissions respectively mounted in the hull of the paddle board. The hull of the paddle board also includes a bow, stern and foot pads upon which the operator stands on. The oars pivot around an oar pivot in a longitudinal direction and paddle arms attached to the oars pivot around an arm pivot in a longitudinal direction. The paddle arms terminate in at a lower at a paddle so that when the operator urges the oars in a rearward and forward motion, the paddle arms pivot around an arm pivot and propel the paddle board.

Abstract: Disclosed herein is a method of water board propulsion comprising placing a buoyant board with a flexible water catching pocket having an open proximal end and at least a partially closed distal end affixed to a bottom surface of the water board in a current of water moving at a speed which is faster than the buoyant board; positioning said open proximal end to receive the flowing water; receiving water flow into the open proximal end; and, accelerating the board in the direction the current with greater acceleration than the same board without a water catching flexible pocket.

Abstract: A recreational water flotation device includes a central body defining an upper surface and a bottom surface and having a front end and a rear end. A left lateral element extends from a left end of the central body and defines a left canted surface canted toward the central body and further defines a left end of the flotation device. A right lateral element extends from a right end of the central body and defines a left canted surface canted toward the central body and further defining a right end of the flotation device. The device is buoyant in water. A propeller can be mounted to the bottom surface of the central body.

Abstract: A personal water craft (PWC) dock has a molded platform, the platform having a main section with its upper surface contoured to provide an elongate recess extending the length of the platform. The recess is shaped and dimensioned to receive and support the hull of a PWC, the recess being asymmetrically located towards one side of the platform. A raised walkway deck section extends the length of the platform and is located towards the other side of the platform, the walkway deck section being located over a buoyancy chamber. The molded platform is configured at each end of the recess for selective installation of a centering roller or a bow stop as desired for convenience when siting the PWC dock and its walkway deck section in relation to a main dock.

Abstract: An indicator to be snapped onto an inflator to indicate the “ready” operating condition of the inflator and, upon firing of the inflator by jerking the jerk handle to pivot the firing lever, the firing lever pops off the indicator from the inflator, thereby indicating the “fired” inoperable operating condition.

Abstract: A pass-through connection for a wall of a drysuit, comprising, a port comprising, a first, exterior port portion encircling a depending cylindrical flange defining a passage through at least a portion of the port and encircling a longitudinal axis of the passage, the first port portion having an exterior end with a first cylindrical recess that encircles and opens onto the passage, the first port portion having two bosses each extending over a different one of opposing sides of the first cylindrical recess to form an undercut below each boss, the two bosses not extending over the passage, the depending flange extending through a hole in the wall of the drysuit which hole is within a periphery of the first port portion; a second, interior port portion encircling the depending flange and connected to the depending flange to form a fluid tight connection, the first and second port portions having at least one rib on one port portion encircling the passage and at least one corresponding recess on the other port p

Abstract: An underwater communication system comprises a plurality of location and messaging units for sending and receiving ultrasonic energy through water. In accordance with one aspect, each of the location and messaging units comprising an array of transducers, a transceiver adapted to generate a code element, generate a data element, generate a modulation element, and combine the code element, the data element and the modulation element into an analog wave form. The system is further adapted to transmit the analog wave form through one of the ultrasonic transducers and receive the analog wave-form generated by at least one of the location and messaging units.

Abstract: An autonomous underwater vehicle (AUV) is configured to record seismic signals during a marine seismic survey. The AUV includes a body having a base (B) and first and second sides (A, C), the body having a head part and a tail part; a propulsion system for guiding the AUV to a final target on the ocean bottom; a seismic sensor configured to record seismic signals; and an anchoring system configured to rock or twist the base in a given sequence so that the base (B) penetrates into the ocean bottom.

Abstract: The invention relates to an arrangement for multi screw vessels, in particular twin screw vessels, with external propeller shafts, as well as to a method for producing such an arrangement. The arrangement according to the invention is in particular suitable for a drive system of an above-mentioned multi screw vessel and to improve the energy efficiency thereof.

Abstract: A propulsion system (102) for an aquatic vessel (100) is provided. The propulsion system includes a plurality of Magnus-type rotors (108) and a drive arrangement (147) for rotating the plurality of Magnus-type rotors. The plurality of Magnus-type rotors are operable to rotate about corresponding substantially upright axes. The propulsion system also includes a control arrangement (150) for controlling the drive arrangement to vary rates of rotations of the plurality of Magnus-type rotors. Each of the plurality of Magnus-type rotors includes a hollow region (116) therein. Each of the Magnus-type rotors is rotationally supported onto a support arrangement (118) which extends into the hollow region. The drive arrangement includes at least one motor (148) disposed in the hollow region and located outside the support arrangement such that the at least one motor is accessible for maintenance.

Abstract: An unmanned, autonomous, ocean-going vessel including a primary hull and a rigid wing rotationally coupled with the primary hull that freely rotates about a rotational axis. At least one of the primary hull and the rigid wing includes at least one selectively floodable compartment configured to selectively flood to submerge the primary hull and at least a portion of the rigid wing. The vessel further includes at least one controller configured to maintain a desired heading. The vessel further includes a control surface element configured to aerodynamically control a wing angle of the rigid wing based on a force exerted by wind on the control surface element. The vessel further includes a rudder. The at least one controller is further configured to determine a rudder position and generate a signal to position the rudder. The vessel further includes a keel coupled with the primary hull.

Abstract: An integral sail to generate a propulsion following a thrust from the wind has an integral layered structure delimited externally by a first external layer and by a second external layer, both made with a smooth layer of thin and continuous film of flexible material. Furthermore, to each of said first external layer and second external layer at least a layer of parallel fibers, adjacent to each other, is associated internally with respect to the layered structure. The whole is made solid by means of at least a layer of thermofusible glue, disposed inside the external layers and in coordination with the corresponding layers of parallel fibers.

Abstract: A piston water jet propulsor for propelling marine vehicles employs the concept of the Side-Intake of water and generates thrust through piston's reciprocating motion in cylinder. The concept of the Side-Intake opens water intake holes on the side and near the discharge end of the cylinder wall with a rotational and electric-magnetic actuated valve to control the intake holes open for water intake or closed during water discharge through the nozzle at the end of the cylinder. The principle feature of the Side-Intake is the separation of the cylinder into a dry and a wet compartment at any time piston moves. The dry compartment is always at atmospheric condition, which allows the piston encounters only air resistance during its recovering stroke. The Side-Intake Piston Water Jet Propulsor requires at least a 2-cylinder system to maintain a continuous water intake and discharge. The preferred embodiment is a Side-Intake Piston Water Jet Propulsor with 4 cylinders.

Abstract: An acceleration control system for a marine vessel includes an actual propulsion power detector, a setting controller configured or programmed to set final target propulsion power of the marine vessel, and a controller. The controller is configured or programmed to set target propulsion power of the marine vessel at an initial time to an initial target propulsion power, to change the target propulsion power of the marine vessel based on an actual propulsion power of the marine vessel and the initial target propulsion power, and to control a propulsion device such that the actual propulsion power of the marine vessel gets closer to the final target propulsion power.

Abstract: Disclosed are a system for analyzing ship ballast water treatment big data using a mobile communication network, the system including: a ship ballast water treatment controller installed in a ship side to record and store operation information of the ballast water treatment system in the ship; a mobile communication network connector installed in the ship side to detects a mobile communication network connectable area from a ship running area, to perform automatic call connection when the ship reaches the mobile communication network connectable area, connects with the ship ballast water treatment controller through the internal communication repeater to transmit the information operation information of the ballast water treatment system recorded in the ship ballast water treatment controller to a ship ballast water operation server in an external internet, and to receive operation and maintenance information of the ballast water treatment system from the ship ballast water operation server; a ship ballast wa

Abstract: The water sports board carrying system is adaptable to paddle boards, surfboards, sailboards, and similar devices. The carrying system includes forward and rearward strap attachment fittings installed along one edge or rail of the board equidistant from a lateral line through the center of gravity of the board. This allows the board to be balanced when carried by a strap attached to each of the fittings. The strap attachment fittings are recessed into the edge of the board to preclude any protrusion that might catch on some article in use or injure a person carrying the board. An example of such strap attachment fittings comprise receptacles permanently secured into the board, having a diametric pin or rod installed across the space defined within each of the receptacles. The shoulder strap can have a snap hook at each end for removable attachment to the pin or rod in each receptacle.

Abstract: A door stop element for an aircraft door has a body which is formed at least approximately L-shaped, and which has at least one contact area on the outer side of one of the legs for fixed contact on the aircraft fuselage, and a stop surface on the inner side of the other leg for the aircraft door. The body has a cavity, on the inner side of which adjacent to the stop surface a rib is provided, which extends through the stop surface symmetrically on both sides of the longitudinal median plane that extends perpendicular to the stop surface.

Abstract: A system and method for heat shielding an inner wall of a fan duct of an aircraft nacelle from engine heat. The system may include a heat shield and an insulation blanket. The heat shield may have a first layer of high temperature composite material bonded to a first surface of an insulant material and a second layer of high temperature composite material bonded to a second surface of the insulant material. The first layer of high temperature composite material may also be bonded to the inner wall. The insulation blanket may be positioned between the heat shield and the engine, and may be fastened to the heat shield and/or the inner wall.

Abstract: An upper attachment system for a trimmable horizontal stabiliser actuator (THSA) comprises: a housing, holding a yoke and a ballscrew; a nut coupled to the housing and cooperating with the ballscrew such that rotation of the ballscrew relative to the nut results in linear motion of the ballscrew; a recess formed between the yoke and the ballscrew and arranged to receive, in use, an upper part of a tie bar of the secondary load path of the actuator; and a biasing mechanism arranged such that, in use, when no axial load is applied to the tie bar, the yoke and the ballscrew are held by balanced forces from the biasing mechanism in a position within the recess.

Abstract: An actuation assembly includes a first shaft comprising a first end disposed opposite a second end. The actuation assembly further includes a second shaft with a first end disposed opposite a second end. The first end of the second shaft is disposed within the second end of the first shaft such that the first end of the second shaft can move relative the second end of the first shaft. A fluid chamber formed between the first shaft and the second shaft at the second end of the first shaft. Magnetorheologic fluid is disposed inside the fluid chamber and a magnetic field generating coil is disposed around the second end of the first shaft and the first end of the second shaft.

Abstract: Systems, methods, and devices are provided that provide hybrid flow control for a simple hinged flap high-lift system using sweeping jet (SWJ) actuators for active flow control (AFC) and adaptive vortex generators (AVGs) that may be actuated by flap deflection for passive flow control (PFC). The various embodiments may significantly reduce mass flow, differential pressure, and power requirements for equivalent flow control performance when compared to using AFC only. The various embodiments may reduce the power requirement of AFC, while still maintaining the aerodynamic performance enhancement necessary for high-lift applications using a simple hinged flap. The various embodiments may provide the necessary lift enhancement for a simple hinged flap high-lift system, while keeping the pneumatic power requirement (mass flow and pressure) for the AFC within an aircraft's capability for system integration.

Abstract: An aerial vehicle system includes a flight system configured to generate propulsive force and lift, a protective framework, and an attachment mechanism secured to the protective framework and configured to selectively attach to a structure to provide stable perching of the aerial vehicle system. The attachment mechanism is an electro-permanent magnet device or a talon-like grip. The flight system is at least partially enclosed by the protective framework.

Abstract: The invention relates to an aircraft landing gear, particularly a front landing gear with at least one EHDC unit, which has at least one electric motor and at least one hydraulic pump, whereby at least one adjusting device is provided for the adjustment of the position of the aircraft landing gear, whereby the adjusting device comprises at least one actuator for driving the adjusting device, whereby the steering angle and/or the steering speed and/or the retraction speed and/or the extension speed and/or the end position damping and/or the position of the adjusting device can be controlled or adjusted by means of the electric motor driving the at least one actuator of the adjusting device by means of the hydraulic pump.

Abstract: The present disclosure describes systems and methods for retractable landing gear. A landing gear arrangement may comprise: a trailing arm; a shock strut; a link rotatably coupled to a first end of the shock strut and rotatably coupled to the trailing arm, the link including a pivot; a rotatable latch rotatably coupled to the link; and an actuator coupled between the rotatable latch and the trailing arm, the rotatable latch configured to rotate about the pivot, the pivot located between a first end and a second end of the rotatable latch, the rotatable latch configured to rotate in a first direction in response to the actuator extending and configured to rotate in a second direction in response to the actuator compressing.

Abstract: Landing gear for an aircraft, the landing gear having at least one pair of shock absorbers comprising a first shock absorber and a second shock absorber, each shock absorber comprising a cylinder defining an inside space and a rod carrying a piston, the inside space being subdivided at least into a “primary” chamber and into a “secondary” chamber, the shock absorber including at least one throttling orifice putting the secondary chamber into fluid flow communication with the primary chamber. The primary chamber of the first shock absorber is connected to the secondary chamber of the second shock absorber of the pair by a first pipe, and the secondary chamber of the first shock absorber of the pair is connected to the primary chamber of the second shock absorber of the pair by a second pipe.

Abstract: A method of isolating vibrations between vibrating bodies includes determining a pressure differential between a first fluid chamber and a second fluid chamber of a liquid inertia vibration eliminator (LIVE) unit, and selectively injecting fluid into or withdrawing fluid from the LIVE unit based on the pressure differential. A system for isolating vibrations between bodies includes a vibration isolator including fluid, a fluid regulator valve in fluid communication with the vibration isolator to selectively flow fluid through the vibration isolator, a pressurized fluid source in fluid communication with the fluid regulator to supply fluid to the fluid regulator, a controller in signal communication with the fluid regulator to control fluid flow between the fluid regulation valve and the vibration isolator, and at least one sensor in signal communication with the controller.

Abstract: Disclosed is a drone having at least one rotor. The at least one rotor comprises a mast and at least two blades having a proximal end and a distal end. The at least two blades are arranged in connection with the mast by their proximal ends. The at least one of the blades comprises an electrically conductive element extending a distance D between its distal end and its proximal end. The electrically conductive element is electrically coupled with means for stopping the blades, thus forming an electrical circuit. The means for stopping the blades is arranged to be actioned when at least one electrical property of the electrical circuit change.

Abstract: A cable cutter (10) for an aircraft (27) comprises an electrically-conducting body (12) configured to be mounted on an aircraft (27) and to cut a cable and an electrically-conducting auxiliary member (38) attached to, and electrically isolated from, the body (12). The body (12) and auxiliary member (38) are configured to together form an antenna. A method of manufacturing an antenna for an aircraft comprises the steps of providing a cable cutter (10) for an aircraft, the cable cutter comprising an electrically-conducting body (12) configured to be mounted on an aircraft (27) and to cut a cable; providing an electrically conducting auxiliary member (38) and attaching it to the body (12) so as to be electrically isolated from the body (12); and providing an antenna connector (42) and connecting the terminals thereof to the body (12) and auxiliary member (38) respectively.

Abstract: An abutment mechanism for a lift assembly of an aircraft. The abutment mechanism comprises a single rigid link having variable travel, the link comprising a rod and a body, the rod being movable in translation relative to the body along the longitudinal direction through said travel, the abutment mechanism including a movement member for adjusting an amplitude of the travel as a function of at least one predetermined parameter, the link having two endpieces suitable for being hinged respectively to a said lift assembly and to a said drive system.

Abstract: A rotor blade assembly includes a rotor blade comprising an inboard end and an outboard end. A composite yoke fitting made from a composite material is attached to the rotor blade. The composite yoke fitting includes an outboard portion inserted into the inboard end of the rotor blade, an inboard portion, and a flexure region about which the rotor blade is configured to flex. The inboard portion and the flexure region are outside the rotor blade.

Abstract: In an embodiment, a layer material configured to be arranged on a rotor blade tip of a helicopter comprises at least one light emitting or reflecting section that emits or reflects light after being exposed to a remote light source. The light source can be arranged on the body of the helicopter.

Abstract: A rotorcraft having a body and a propulsion system wherein the propulsion system includes a main thrust rotor and multiple control rotors, wherein the main thrust rotor is coupled to the body, whereby the main thrust rotor is driven by a main thrust drive shaft having an axis of rotation maintained in a fixed orientation to the body of the rotorcraft and wherein the multiple control rotors are arranged to control roll, pitch and yaw of the rotorcraft and are driven by respective control drive shafts offset to the axis of rotation of the main thrust drive shaft.

Abstract: An unmanned vehicle receives a message from another unmanned vehicle. The recipient unmanned vehicle uses information included with the message to determine whether a quorum of other unmanned vehicles have vetted information in the message. If a quorum of unmanned vehicles have vetted the message, the unmanned vehicle uses the information in the message to determine how to perform one or more operations.

Abstract: An unmanned vehicle determines how to perform a task based at least in part on a message received from another unmanned vehicle. At a later time, the unmanned vehicle detects that the other unmanned vehicle has become untrusted. The unmanned vehicle recalculates how to perform the task such that the recalculation is independent of any messages from the other unmanned vehicle. The unmanned vehicle may also transmit messages to other unmanned vehicles to provide notification of untrustworthiness of the other unmanned vehicle.

Abstract: A multi-purpose craned air transporter (CAT) that is structurally configured to manage liabilities, and to expedite independent functions for hauling and craning operations. The CAT assembly is multi-purpose for ground and air operations with the necessary attachments to execute each specified operation. The CAT is configured with a top mount for interoperability with a craning device, which shall be attached to a crane or helicopter. The CAT also has a bottom mount to operate with ground transportation. The CAT assembly shall be designed to detach from the confines of a crane, helicopter, or article of ground transportation that may be in control of the assembly to execute a specific operation. The CAT assembly includes altered embodiments to facilitate several different operatives that may require a customized module to achieve maximum effectiveness.