Abstract: A transport system can employ a transport assembly with a main support member attached to a mounting connection, a tow connection, a suspension, and a horizontal articulation mechanism. The horizontal articulation mechanism may be configured to raise the suspension of a ground surface along a first direction and move the main support member in a second direction with the first direction being orthogonal to the second direction.

Abstract: A mobile device mount for vehicles, which is used for fastening on a handle stem of a bicycle, includes a mounting portion, a first holding structure, a second holding structure and a binding structure. The first holding structure is disposed on a surface of the mounting portion to form a holding area. The second holding structure is disposed on the other surface of the mounting portion to form another holding area and has a protruding portion for leaning against the handle stem. The binding structure is connected to the mounting portion and has a binding ring and a binding belt. The binding ring is located at a side of the mounting portion, and the binding belt extends from another side of the mounting portion. Thereby the protruding portion leans against the handle stem, and the binding belt surrounds the handle stem to fasten to the binding ring.

Abstract: A smart bicycle includes various integrated electrical accessories. The bicycle frame has an integrated computer processor, a global positioning system (GPS) receiver, horn and rear light. The stem of the bicycle has an integrated visual display that provides performance and directional information to the user. The fork of the bicycle has integrated lights and the front wheel can have an integrated dynamo generator that can power the electrical components and charge a system battery. The ride data can be transmitted to a smartphone and/or system servers, which can also store, analyze and display the rider data.

Abstract: Provided is a tilting device and method for a vehicle and the vehicle. The tilting device for the vehicle includes a main frame, a steering mechanism disposed on the main frame, a detent mechanism that is disposed on the main frame and the steering mechanism and that is configured to control a tilt angle of the vehicle where the tilt angle is an angle between the vehicle and a first plane, and a control mechanism that is disposed on the vehicle and electrically connected to the detent mechanism and that is configured to control the tilt angle by controlling the detent mechanism.

Abstract: A locking device is provided for a scooter when being telescopically collapsed to lock the steering shaft when being folded and to lock a telescopic front frame when being telescopically collapsed. The locking device includes a steering shaft locking unit is coupled to a pivot seat of a telescopic front frame and a pivot portion of the steering shaft. The steering shaft locking unit is at least provided to hold the steering shaft in place when being in a horizontally folded mode. A front frame telescopically collapsed locking unit includes a first positioning portion disposed on a shank section of the steering shaft and a second positioning portion disposed on one of a rear frame and a foldable seat. The first positioning portion and the second positioning portion are engaged to each other for positioning the telescopically collapsed front frame when the steering shaft is in a horizontally folded mode.

Abstract: A handle includes handle grips and a handle pipe including an attachment portion, a first grip portion, a second grip portion, a first bent portion between the attachment portion and the first grip portion, and a second bent portion between the attachment portion and the second grip portion. The first grip portion includes a first overlapping region overlapping a first handle grip and a first non-overlapping region not overlapping the first handle grip. The second grip portion includes a second overlapping region overlapping a second handle grip and a second non-overlapping region not overlapping the second handle grip. The first and second non-overlapping regions each include a thick portion having a thickness larger than, or equal to, a thickness of the attachment portion. The first and second overlapping regions each include a thin portion having a thickness smaller than the thickness of the thick portion.

Abstract: A handlebar assembly is able to attach to a bicycle. The handlebar assembly provides a higher grasping point for a bicycle operator than the original handlebar, enabling the operator to lean back and assume a recumbent posture while riding. The handlebar assembly includes and attachment member, a handlebar member, and an extension vertically separating the two components. The attachment-member is able to affix about the existing tubular handlebar of the bicycle by means of a clamp.

Abstract: An adjustable hand brake lever assembly for a proportional electric braking system for a bicycle or other vehicle. The brake lever assembly may include a sensor assembly which is adapted for use with a standard brake lever assembly as used with mechanical cable braking systems. The sensor assembly may be replaced as a unit. The sensor assembly is adapted to allow for setting the reach adjustment, allowing a user to set a preferred initial position. The adjustable brake lever assembly may be coupled to a control electronic module and a regenerative braking system on a bicycle.

Abstract: A clipless pedal system is provided. In various embodiments, systems of the present disclosure comprise pedals and cleats for interaction with the pedals. At least one of a pedal and an associated cleat comprises a magnet, and at least one of the pedal and the associated cleat comprises a ferrous metal for interaction with the magnet. Geometric features are provided to enable both a secure connection between a cleat and a pedal and to enable a user-friendly release of the cleat from the pedal.

Abstract: Among others, the present invention provides electric bicycles each including a body frame; a front wheel and a rear wheel; an electric motor configured to provide a mechanical power to at least one of the front and rear wheels; and a battery box configured to removably receive and hold one or more lithium battery packs. The one or more lithium battery packs are configured to power the electric bicycle, and at least one lithium battery pack is capable of being used as a power supply of a separate lithium electric tool.

Abstract: A shifting control device comprises a controller configured to control an actuator of a gear shifting device to arrange a chain guide of the gear shifting device on a plurality of gear positions. The controller is configured to control the actuator to temporarily arrange the chain guide on a first temporary position in a multistage gear shift operation before stopping the chain guide at the first target gear position. The controller is configured to temporarily arrange the chain guide on a second temporary position in a single gear shift operation before stopping the chain guide at the second target gear position. The first temporary position is offset from the second temporary position in the gear shift direction if the first target gear position is the first target gear position and the second target gear position correspond to the same gear position of the plurality of gear positions.

Abstract: A gear shift controller includes a detection circuit and a control unit. The detection circuit is configured to determine traveling state information about a traveling state of a human-powered vehicle. The control unit is configured to receive the traveling state information from the detection circuit to control a shift standby time of a transmission of the human-powered vehicle. The traveling state information includes information other than traveling speed information about a traveling speed of the human-powered vehicle and crank information about crank rotation information of the human-powered vehicle.

Abstract: A mooring rope includes a rope body, a fixing sleeve, and a data carrier. The rope body has two fixed segments and a rope loop between the fixed segments. The fixing sleeve combines the two fixed segments. The data carrier includes a connecting piece, a main body, and a tag member. The connecting piece is arranged in the fixing sleeve. The main body is connected to the connecting piece. The tag member is mounted on the main body. The tag member stores information for an external data reader to read in a non-contacting manner. As such, the data carrier can be firmly fixed on the mooring rope without falling off easily.

Abstract: Disclosed is a novel type of computing apparatus which is integrated within a buoy that obtains the energy required to power its computing operations from winds that travel across the surface of the body of water on which the buoy floats. Additionally, these self-powered computing buoys utilize their close proximity to a body of water in order to significantly lower the cost and complexity of cooling their computing circuits. Computing tasks of an arbitrary nature are supported, as is the incorporation and/or utilization of computing circuits specialized for the execution of specific types of computing tasks. And, each buoy's receipt of a computational task, and its return of a computational result, may be accomplished through the transmission of data across satellite links, fiber optic cables, LAN cables, radio, modulated light, microwaves, and/or any other channel, link, connection, and/or network.

Abstract: The invention discloses a lifeboat which can be used in a typhoon day. The boat includes a hull. The hull is provided with a helical gear space symmetrically on the lower side of the transmission space. On the left side of the energized magnet, when the hull is stabilized, the motor needs to be automatically loosened and taken up to stabilize the hull. At the same time, the fan blades can be rotated to drive the ship forward or backward by the rotation of the helical gear, which can fully convert the excess electrical energy into The mechanical energy can also slide the rotation axis of the fan blade down to the fixed connection with the first rotating rod. When a person steps on the pedal, the mechanical energy generated can drive the fan blade to rotate to make the boat move forward or backward, and a life buoy is also designed. Insufflation function and push-out lever, which can automatically throw out the inflated life buoy for rescue when rescue is needed.

Abstract: A lifeboat launch control system. The lifeboat launch control system has a wheel trunk that runs along the side of a ship. An axle box is vertically movable in the wheel trunk. The axle box has a pair of wheels on opposing sides of a bar. A shaft is removably inserted into the bar. The shaft is removable from the bar by a handle. When the shaft is removed from the bar, the lifeboat is released from the ship.

Abstract: An assembly for storing and transporting compressed fluid, such as compressed natural gas, that includes a plurality of hexagonally stacked pipe stored in a cargo hold in or on a vessel, that includes a lower support, side supports and a forcing mechanism that presses strongly down on the pipes so that they cannot move relative to themselves or the vessel on which they are placed. The friction between the pipes causes the plurality of pipes to act as part of the vessel in terms of its structure. The stacked pipe is supported by a plurality of spacers, such as convex side up pipe segments for maintaining a gap between adjacent ones of said plurality of pipes in a same row in said stacked pipe. A load equalizer may be located above the plurality of pipes for distributing the compressive force from the forcing mechanism.

Abstract: Carry system for personal watercraft is disclosed. In one example, the carry system is used to carry a personal watercraft overhead. In another example, the carry system is used as a seat for the rider of the personal watercraft.

Abstract: A light emitting device (1) is provided that can be used in various contexts, including the context of realizing an anti-fouling action on surfaces. The light emitting device (1) comprises light emitting units (10) being arranged in a plane filling pattern (20) for covering at least a substantial portion of a surface. Individual light emitting units (10) are electrically interconnected through connection areas (12, 13) as present on the light emitting units (10) for providing electrical access to an internal electrical circuit (11) thereof, wherein the light emitting units (10) overlap at the positions of at least portions of the connection areas (12, 13) thereof. Further, it may be so that at least one of the connection areas (12, 13) of the individual light emitting units (10) is electrically connected simultaneously to respective connection areas (12, 13) of at least two other light emitting units (10).

Abstract: There is provided an outboard motor. A first oil passage is provided in a lower case, extends upward from a front lower portion, and reaches a first connection position which is positioned above a height position of an anti-ventilation plate or at a front portion of a boundary portion between a middle case and the lower case. A second oil passage is provided in the lower case or at the boundary portion, extends rearward from the first connection position, and reaches a second connection position which is positioned at a rear upper portion or at the rear portion of the boundary portion. A first oil supply/discharge port is opened on a side surface of the rear upper portion of the lower case or on a side surface of the rear portion of the boundary portion, and communicates with the second oil passage at the second connection position.

Abstract: Door for cargo airplane, wherein a cargo compartment is accessible from the outside of the fuselage through an opening for loading goods provided with the door. The door is provided with a first operating handle accessible from the outside of the door and used to lock/unlock the pins that are used to connect the door to the fuselage and control the closing/opening of a ventilation door; and a second operating handle accessible from the outside of the door for advancing/retracting the pins in/from respective seats. According to the invention, the door is provided with a third handle accessible from the inside of the door and mechanically interconnected with the first handle for locking/unlocking the pins and controlling the closing/opening of the ventilation door; and a fourth operating handle accessible from the inside of the door and mechanically interconnected with the second handle for advancing/retracting the pins in/from respective seats.

Abstract: A locking mechanism for a door panel to be positioned within and out of blocking relationship with an opening. Mechanism includes a deadbolt rotatably connected to the wall and having a curved configuration and a locking bracket connected to the door panel. The locking bracket extends from the door panel in an angular direction with respect to a plane of door panel. With door panel in a closed position and deadbolt in a first position, the locking bracket extends through the curved configuration. Deadbolt is in blocking relationship with the locking bracket in a direction along a plane of the door panel and is not in blocking relationship in a direction along the locking bracket. With door panel in closed position, deadbolt is in a second position not in blocking relationship with the locking bracket permitting door panel to move in a direction along a plane of the door panel.

Abstract: To facilitate the assembly of the wing unit of an aircraft, this wing unit includes two wings each having a lateral wing box extended toward the interior by a center wing box half having an interior end, the two wings being attached to one another using attachment bolts linking the two interior ends of the two center wing box halves, and passing through an intermediate wall connecting two fuselage frame walls.

Abstract: An apparatus and its method of use provide a preload to the assembly of large structures, for example the assembly of an aircraft wing panel to an aircraft wing frame. The apparatus and its method of use preloads the aircraft wing panel of the aircraft wing structure and presses the aircraft wing panel against the aircraft wing frame of the aircraft wing structure, temporarily securing the aircraft wing panel against the aircraft wing frame and indexing the aircraft wing panel to the aircraft wing frame for the installation of permanent fasteners securing the aircraft wing panel to the aircraft wing frame.

Abstract: An aircraft flow body comprising a rib bounded by and fixedly attached to an outer skin, wherein the outer skin and the rib are configured to plastically deform when the outer skin is subjected to an impact load in a leading edge region of the airflow body, wherein the stiffness of the outer skin is greater than or equal to the stiffness of the rib when deformed by the impact load.

Abstract: A leading edge slat of a wing element of an aircraft. The aircraft defining a mark including a main fuselage axis x and a spanwise axis y. The wing procuring a lift along an axis z. The wing element having a skin forming the leading edge slat, a spar linked to the skin and a stiffening structure linked on the leading edge side to the spar and to the skin. The stiffening structure being formed from a formed sheet metal having a plurality of bosses distributed according to the length of the leading edge. The bosses extending between the spar and the inner face of the skin.

Abstract: A connection rod comprising first and second connection elements. The first element comprises a shaft, a first connector at a shaft proximal end and a piercing body at a shaft distal end. The second element comprises a hollow casing with a fluid barrier therein, which, when intact, forms first and second reactive fluid material reservoirs, both within the casing. The second connection element comprises a second proximal end connector and a distal end inlet hole to the second reservoir. The piercing body fits within the casing and the shaft slidably engages the inlet hole such that the first element slides relative to the second element. The piercing body pierces the fluid barrier such that the reactive fluid materials mix between the reservoirs and react to form a reacted solid material restraining the piercing body within the casing to prevent relative sliding between the first and the second connection elements.

Abstract: Technologies for providing blended wing body aircraft control surfaces are described herein. In some examples, one or more of the control surfaces have angular configurations that reduce the formation of air vortexes when in upward or downward configurations, thereby reducing the drag on the aircraft when the control surfaces are being used.

Abstract: An actuator assembly for moving an aircraft wing tip device is disclosed. The wing tip device is rotatable about a hinge axis relative to a fixed wing of the aircraft. The hinge axis is orientated non-parallel to a line-of-flight direction of the aircraft. The actuator assembly includes a primary shaft having an axis of rotation orientated substantially parallel to the line-of-flight direction, a motor to cause rotation of the primary shaft, and a secondary shaft orientated substantially parallel to the hinge axis. The secondary shaft is couplable to the primary shaft and is arranged to rotate the wing tip device in response to the rotation of the primary shaft.

Abstract: A drone according to the present invention comprises one or more reverse thrust propeller units for generating reverse thrust and, when an operation such as the horizontal delivery of an object is performed, quickly offsets the movement of the center of gravity by using the force of reverse thrust such that the force applied to each propeller can be balanced. Propeller supports having the reverse thrust propeller units mounted thereon can be formed such that the lengths thereof can be extended and reduced. Since rotational force applied to each propeller motor can be equally distributed, stable flight can be promoted, and the risk of crash produced according to the application of excessive force can be reduced. Therefore, the present invention is applied to various fields in which the center of gravity changes because of load applied to one side, and thus stable operation of the drone can be promoted.

Abstract: Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

Abstract: Systems and methods for mechanically rotating an aircraft about its center-of-gravity (CG) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

Abstract: A vibration suppression unit for an aircraft comprising a mass assembly having a center of mass and a frequency rotor having a frequency center axis offset from a central axis of rotation and driven to rotate about the central axis, a vibration control amplitude rotor rotationally coupled to the mass assembly and having an amplitude center axis offset from the central axis driven independently of the frequency rotor to rotate about the central axis, the amplitude center axis and the frequency center axis having a selectively variable displacement angle defined by an inclusive angle between a line extending between the central axis and the amplitude center axis and a line extending between the central axis and the frequency center axis, wherein the amplitude rotor and the frequency rotor are controllable to produce a vibration control force vector having a controllable magnitude and frequency about the central axis of rotation.

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.

Abstract: A system for driving a tilt rotor between vertical and horizontal using a variable displacement motor controlled in response to a swash angle of the motor measured in a feedback loop.

Abstract: A wingless compact aircraft, with limited footprint and no exposed high-speed moving parts. The aircraft can takeoff and land vertically, can fly at high-speed and even cruise on land and water in one of the preferred embodiments.

Abstract: A multi-modal vehicle includes a frame, a rotor pivotally mounted to the frame, the rotor including a first position and a second position circumferentially spaced from the first position, and a motor coupled to the rotor and configured to rotate the rotor, wherein, when the rotor is disposed in the first position, the rotor is configured to generate lift when actuated by the motor, wherein, when the rotor is disposed in the second position, the rotor is configured to engage a surface to transport the vehicle when actuated by the motor.

Abstract: Apparatuses for securing drones during transport and methods of use are disclosed herein. An example apparatus includes a structural panel of a vehicle having a compartment configured to receive and retain a drone, a retractable cover member configured to at least partially cover the compartment to create an enclosure around the drone, and a drone securement assembly that retains the drone within the enclosure so as to prevent the drone from displacement during vehicle operation.

Abstract: This unmanned aerial vehicle has: a main body; a plurality of rotary wings provided on the main body; a wire for suspending an object from the main body; a hook attached to the wire; a winch for rotatably supporting a spool on which the wire is wound in the forward and backward directions, winding the wire by rotating the spool in the forward direction and unwinding the wire by rotating the spool in the backward direction; and a controller for restricting the backward rotation of the spool when the tension of the wire becomes less than a first threshold value, and restricting the forward rotation of the spool when the tension of the wire becomes less than the first threshold value and becomes equal to or less than a second threshold value, which is less than a gravitational force acting on the hook.

Abstract: Particular embodiments described herein provide for modular device assemblies and methods for enabling maintenance and servicing, particularly by an unmanned aerial vehicle. A device assembly comprises a plurality of modules, each module having control circuitry, a communications port and contact points to couple the modules. When the modules are coupled, the communications ports are connected to create a bus for communications between the modules. The modular device structure where modules are removable and replaceable allows for an unmanned aerial vehicle to perform maintenance on the device.

Abstract: An example UAV landing structure includes a landing platform for a UAV, a cavity within the landing platform, and a track that runs along the landing platform and at least a part of the cavity. The UAV may include a winch system that includes a tether that may be coupled to a payload. Furthermore, the cavity may be aligned over a predetermined target location. The cavity may be sized to allow the winch system to pass a tethered payload through the cavity. The track may guide the UAV to a docked position over the cavity as the UAV moves along the landing platform. When the UAV is in the docked position, a payload may be loaded to or unloaded from the UAV through the cavity.

Abstract: Embodiments described herein are methods and systems that relate to delivery of a payload to a particular delivery surface. A payload is collected at a first physical location using a retractable delivery mechanism of a UAV, and the UAV flies to a designated second physical location, whereupon sensor data is obtained using one or more sensors of the UAV. The sensor data is used to obtain characteristics of an area which may be used as a delivery surface at the second physical location. An actual delivery surface is selected based on criteria in the form of rule data specifying an appropriate delivery surface and the sensor data. Once the delivery surface has been selected the retractable delivery lowers the payload towards the selected delivery surface.

Abstract: A cargo loading system includes a drive unit extending along a length of a cargo area of an aircraft. The drive unit is configured to couple to a modular cargo structure via a handling member and to convey one or more cargo items coupled to the modular cargo structure. The cargo loading system further includes a rotation device and a driver. The rotation device is in contact with the drive unit. The driver is configured to apply torque to the rotation device to cause the drive unit to move the modular cargo structure within the aircraft.

Abstract: Technologies for providing emergency egress routes for a blended wing body aircraft are described herein. In some examples, the emergency egress routes are through a side cabin bulkhead and aft one or more cargo holds. In some examples, the blended wing body aircraft has wings that are high geometry wings. In these examples, the emergency egress routes do not penetrate an aft spar, reducing weight and increasing the integrity of the aircraft.

Abstract: The aircraft has at least one power electronics component and a cooling circuit for cooling the at least one power electronics component by means of a fluid, wherein the aircraft has temperature adjusting means which are designed and arranged to adjust a temperature of the cooling circuit as a function of a temperature in or on the aircraft or of a power loss.

Abstract: A number of devices are provided for detecting presence of ice in an airstream. In some examples such device includes a housing defining a first chamber and a second chamber, and a partition wall separating the first chamber and the second chamber. The first chamber has at least one inlet opening on a front housing wall facing the airstream, and at least one outlet opening, smaller than the at least one inlet opening. The second chamber is configured for being operatively coupled to at least one electromagnetic (EM) system that is configured for transmitting EM energy to the first chamber at least via the partition wall, which is transparent and/or translucent with respect to the EM energy, the EM energy being configured for melting ice that can accrete with respect to the inlet opening.

Abstract: An ice protection system for controlling icing on an aircraft surface includes an OAT sensor configured to provide a signal indicative of an OAT, a LWC detector configured to provide a signal indicative of a LWC, an electrothermal device located on the aircraft surface, and an electronic control system configured to determine a critical temperature (TC) at or below which an anti-icing system will be used to preheat the aircraft surface, supply an electrical power having a calculated power level to the electrothermal device, and calculate the power level as being: zero if OAT>TC and LWC=0, controlled based on OAT and LWC if OAT>TC and LWC>0, controlled based on OAT and LWC if OAT<TC and LWC>0, and controlled based on OAT if OAT<TC and LWC=0.

Abstract: A parachute deployment system is disclosed. In various embodiments, the system includes an interface configured to receive sensor information; a parachute load limiting device; and a parachute load limiting device state controller. The parachute load limiting device state controller sets a state of the parachute load limiting device to a state associated with a corresponding amount of load based at least in part on the sensor information.

Abstract: A propulsion assembly for an aircraft, comprising a pylon to be secured below a wing of the aircraft and having a front face and a lower face, and a turbomachine comprising, from upstream to downstream in a direction of a flow of air passing through the turbomachine during operation, a fan and an engine driving the fan. The fan is faired by a fan casing and the engine is faired, from upstream to downstream, by an intermediate casing and an engine casing, the intermediate casing having a hub and an outer ring extending the fan casing, the ring being spaced apart radially from the hub and secured to the latter by arms extending in an air duct. The propulsion assembly comprises a front engine attachment secured between the pylon front face and the hub and a rear engine attachment secured between the pylon lower face and the engine casing.

Abstract: An aspect includes a system for pre-start motoring control for multiple engines of an aircraft. The system includes a first engine starting system of a first engine and a controller. The controller is operable to control a motoring time of the first engine starting system relative to one or more other engine starting systems of one or more other engines of the aircraft by adjusting the motoring time of the first engine starting system within a tolerance of the motoring time of the one or more other engine starting systems in a pre-start motoring sequence.