Abstract: A brake for a bicycle includes a base, first and second arm assemblies. The first and second arm assemblies are pivoted to the base. The first arm assembly has a first end portion, for connection of a brake line a second end portion for frictionally contacting a brake side of a wheel rim. The second arm assembly is pivoted to the base and corresponds to the first arm assembly. The second arm assembly has a third end portion, a fourth end portion and a second abutting portion which is arranged on the third end portion. The second abutting portion is located correspondingly above the first abutting portion and interferable with the first abutting portion in a pivoting direction of the first abutting portion. The fourth end portion is swingable toward the brake side to clip the other brake side of the wheel rim.

Abstract: A bicycle hydraulic operation device includes a bracket configured to be attached to a bicycle part. A hydraulic cylinder is provided on the bracket, and a piston is located within the hydraulic cylinder. An attachment bore provided on the bracket, and the attachment bore is connected with the hydraulic cylinder. The attachment bore includes a step. At least part of the attachment bore is arranged in an area that radially surrounds the hydraulic cylinder.

Abstract: A master cylinder for a hydraulic brake comprises a compensating chamber, a cylinder in which a piston is movably disposed, a pressure chamber disposed in the cylinder and connected to the compensating chamber through at least one connecting opening, and a gasket for interrupting the connection between the pressure chamber and the compensating chamber. The gasket seals the compensating chamber and the pressure chamber against the environment.

Abstract: A bicycle hydraulic operating device basically has a base member, an operating member, a piston and a connecting rod. The base member includes a cylinder bore and a reservoir tank. The operating member is pivotally mounted to the base member to pivot about a pivot axis. The piston is movably disposed in the cylinder bore of the base member along a cylinder axis of the cylinder bore. The connecting rod operatively couples the operating member to the piston. The reservoir tank is arranged to overlap the connecting rod as viewed in a direction parallel to the pivot axis of the operating member. The reservoir tank is arranged to at least partly offset from the cylinder bore in a direction parallel to the cylinder axis.

Abstract: An electrically assisted bicycle includes an electric motor which applies a walk-push assisting torque to a rear wheel of the bicycle when a rider propels the bicycle by pushing it while walking, and a motor controller configured or programmed to execute a first mode in which the electric motor applies no torque to the rear wheel, a second mode in which the electric motor applies to the rear wheel a stay assisting torque which causes the electrically assisted bicycle to stay in a position where the rider wants to stay, and a third mode in which the electric motor applies the walk-push assisting torque to the rear wheel, wherein the first mode, the second mode, and the third mode are able to be selected by using an operator able to be operated by the rider.

Abstract: A bicycle rear derailleur is provided, which includes a base adapted to be mounted on a bicycle frame, a movable member, a linkage assembly pivotally connected to and between the base and the movable member, a pivot shaft provided within and pivotally rotatable relative to the movable member, a chain guide fixed to an end of the pivot shaft, a restriction assembly provided on the pivot shaft, and a friction assembly provided within the movable member to provide a rotational friction on the restriction assembly. Whereby, the chain guide is pivotally awing toward a first direction by a force; when the chain guide swings toward a second direction which is opposite to the first direction by another force, it is forced by a swing resistance.

Abstract: An electric motorcycle includes an electric motor, a motor controller for controlling the operation of the electric motor, a gearbox that can be of a used or new fuel engine-based vehicle and rotatable by the electric motor, and a main drive shaft coupled between the electric motor and the gearbox. Subject to the optimal power transmission performance of the gearbox, the electric motor is capable of producing the most appropriate driving speed in the starting state or any of a variety of travelling states, achieving optimal output efficiency and significantly reducing power consumption and enhancing endurance.

Abstract: Various embodiments are disclosed for a stepped cambered planing hull for a boat including a swept back cambered planing surface having a non-linear distribution of camber. The non-linear distribution of camber along the swept back cambered planing surface may enable stepped cambered planing hulls having high deadrise (i.e., greater than 15 degrees). The stepped cambered planing hull may include a shaped hydrofoil that generates further hydrodynamic lift by piercing the free surface wake produced by the swept back cambered planing surface. The stepped cambered planing hull may have external bottom surfaces adapted at the after-body and transom to accommodate a distinctive profile of the free surface wake produced by the swept back cambered planing surface. The stepped cambered planing hull may include an adjustable interceptor blade to regulate hydrodynamic lift at low speeds or to ensure an optimal dynamic trim angle in a wide range of speeds.

Abstract: A cleat for a boat includes a cam mounted to the boat, where the cam has a rotatable toothed surface for pressing against a line. The cleat also includes a guide mounted to the boat adjacent the cam, where the guide has a surface for directing the line above a top of the cam. In addition, the cleat has a slot formed in the surface of the guide, which permits the line to be moved into opposition with the rotatable toothed surface of the cam.

Abstract: An emergency ship arrest system includes a vessel attachment system, a retrieving system, and an anchor system. The vessel attachment system is configured to connect to a vessel at sea, and includes a bridle system and a hawser line. The bridle system is operatively connected to the hawser line's proximal end. The bridle system is configured to engage at least four fittings on a foredeck of the vessel to distribute the load over the foredeck. The retrieving system includes a retrieving line with a proximal end that is detachably connected to the hawser line's distal end in a setup position. The anchor system includes a main rode and a para sea anchor. The main rode's proximal end is detachably connected to the hawser line's distal end in an anchor position.

Abstract: Oil tanker and or ore/oil carrier can take more good fuel oil consumption through cargo oil handling by usage of electric motor driven system instead of steam turbine driven cargo pump system. Its merit is about 20%.

Abstract: A ladder for a boat includes a rail configured to be coupled to the boat and a rung supported by the rail. A light source is coupled to at least one of the rung and the rail. A power source provides electrical power to the light source, and a water sensor controls provision of the electrical power to the light source. The electrical power is provided to the light source and the light source is illuminated in response to the water sensor sensing water. A lighted rung for a boat ladder is also provided.

Abstract: There is provided a renewable power generation farm for fishing work, the farm comprising: a plurality of mutually connected floating ships, wherein each ship is configured to generate an energy using solar and wind power, wherein each ship comprises: a main elongate floating structure; a wind-based energy generation device secured to the main elongate floating structure; a transverse beam extending perpendicularly to a longitudinal direction of the main structure; a longitudinal beam extending in a parallel manner to the longitudinal direction of the main structure; connection beams connecting both opposing ends of the transverse beam and both opposing ends of the longitudinal beam respectively; auxiliary pillars vertically extending through the both ends of the transverse beam and the longitudinal beam respectively; solar-based energy generation devices disposed at top ends of the auxiliary pillars respectively; and auxiliary elongate floating structures disposed at bottom ends of the auxiliary pillars pass

Abstract: The present invention relates to two configurations of structure for a compact, pedal-propelled boat, a recumbent configuration and a conventional configuration, and to two possible propulsion systems, one with rigid transmission system and other with flexible transmission system. Both configurations are used with hulls arranged in parallel, catamaran configuration, preferably inflatable, allowing the volume and size of the assembly to be reduced so as to fit in a car trunk, making it easier to transport and store. In the recumbent configuration, the boat driver is in a sitting position, with his back supported by the seat, and actuates the pedals located in the front part of the structure while maneuvers the boat by means of handlebars located on the sides of the structure. In the conventional configuration, the boat driver is in the same position as the rider of a conventional bicycle, and the seat, pedals and handlebar are arranged in the same positions as in a bicycle.

Abstract: To display a multidimensional code representing unique information of an outboard motor, a display device ensures switchably displaying the multidimensional code representing identical information by a plurality of display patterns where ease of reading is mutually different. A multidimensional code creating unit converts the unique information of the outboard motor into the multidimensional code and creates the multidimensional codes by two patterns. That is, a first multidimensional code creating unit creates a multidimensional code for a display pattern that represents the unique information of the outboard motor by the predetermined count of N (one or plural) multidimensional codes.

Abstract: A ship propulsion device (1) is adapted to rotate a propeller (20) to propel a ship (2). In a case where the rotating speed of the propeller (20) is less than a predetermined rotating speed, a low-output sub-motor (M2) is controlled and rotationally driven by a small-capacity general-purpose inverter (24), and the rotational driving is transmitted to the propeller (20) so as to rotate the propeller. In that case, in a drive system of a main motor (M1), rotation is not transmitted to a slip clutch (23) or an input shaft (7) by cutting off an on-off clutch (8). In a case where the rotating speed of the propeller (20) becomes equal to or more than the predetermined rotating speed, a driving source is switched from the sub-motor (M2) to the main motor (M1) so as to couple the on-off clutch (8), and the rotating speed of the main motor (M1) is controlled by the slip clutch (23) and transmitted to the propeller (20) so as to rotate the propeller (20).

Abstract: Disclosed is a water intake system for a floating vessel in a body of water, which includes within the hull of the vessel an intake compartment for taking in water from the body of water and a distribution compartment for distributing and supplying the water to one or more consumer units within the floating vessel. The intake compartment is arranged below a lowest operational draught of the vessel and has an inlet in a bottom region of the intake compartment. The intake compartment is coupled by a conduit to the distribution compartment for allowing water to flow into the distribution compartment. The water intake system further includes a water lift hose that is connected to the inlet and is extendible below the hull of the vessel.

Abstract: Arrangements described herein relate to apparatuses, systems, and methods for a housing of an unmanned aerial vehicle (UAV), the housing includes but is not limited to a metallic porous material having a shape of an enclosure of the UAV, and a phase change material (PCM) provided in at least a portion of the metallic porous material. The metallic porous material and the PCM are configured to passively cool the UAV.

Abstract: A latching mechanism is provided for engaging an aircraft surface panel to a support member. The aircraft panel is provided with a post extending from the lower surface, which extends through a panel support member into a post engagement mechanism. The post engagement mechanism defines a rotatable sleeve, which rotates for locking and unlocking engagement between the post and the post engagement mechanism. Locking engagement continues when power to the post engagement actuator is terminated. The post engagement mechanism may utilize various types of actuators, including mechanical, hydraulic, and pneumatic. The aircraft panel and the panel support member are translatable into and out of abutting engagement independent of the need for any contact with the aircraft panel upper surface.

Abstract: A system for opening a door of an aircraft includes a connection assembly adapted to connect the door to a fuselage section of the aircraft. The connection assembly includes a main hinge pivotally connected to the fuselage section and a link assembly connecting the door to the main hinge and pivotally connected to the fuselage section, the link assembly including one member slidingly and pivotally connected to the door. The system also includes a latch mechanism between the door and the main hinge, the latch mechanism being adapted to be actuated. The system is adapted to move the door upwardly and inwardly along a predetermined path without moving the main hinge through movement of the latch mechanism and, subsequently, to pivot the door around a virtual pivot point located outside of the aircraft by moving the main hinge once the door has reached an end of the predetermined path.

Abstract: A passenger aircraft including a wing (1) and a wing tip device (3). The wing tip device (3) is moveable between a flight configuration for use during flight and a ground configuration for use during ground-based operations. In the ground configuration the wing tip device is folded downwardly from the flight configuration such that the span of the aircraft is reduced. The wing tip device (3) is connected to the wing along a hinge (9) defining a hinge line (11). The hinge (9) may be arranged to prevent the wing tip device (3) rotating upwardly beyond the flight configuration. The hinge line (11) may be orientated at an angle to the flight direction such that the wing tip device (3) presents a larger frontal area when it is in the ground configuration than when it is in the flight configuration, such that aerodynamic forces urge it to rotate about the hinge line (11) away from the ground configuration and towards the flight configuration.

Abstract: Aspects of the disclosure are directed to a nacelle of an aircraft, comprising a surface that is profiled such that during cruise flight operation lines of constant static pressure of a boundary layer around the nacelle in a given region are substantially contained within a plane that is normal to an engine axis.

Abstract: Examples of rotor speed reduction using a feed-forward rotor speed control command are provided. In one example, a computer-implemented method includes: receiving, by a processing device, flight command indicative of a change in a flight characteristic of an aircraft comprising a rotor; generating, by the processing device, a change in load factor based on the flight command; generating, by the processing device, a change in rotor speed based on the change in load factor; generating, by the processing device, a rotor speed command based on the change in rotor speed to a flight controller to cause the aircraft to change a rotor speed of the rotor; and changing, by the processing device, the rotor speed of the rotor responsive to the rotor speed command.

Abstract: A landing gear platform is positionable between rearward and forward tires on one side of an aircraft landing gear and rearward and forward tires on the opposite side of the aircraft landing gear. The platform includes a pair of chocks that engage between the rearward and forward tires on the one side of the aircraft landing gear and the rearward and forward tires on the opposite side of the aircraft landing gear and prevent the tires from rotating. A panel spans over the tops of the pair of chocks. A top surface of the panel can be reached by a worker using a stepstool, enabling the worker to stand on the top surface of the panel when performing work on the landing gear above the rearward and forward tires of the aircraft landing gear.

Abstract: A resonator provided with a heavy member comprising a casing fastened a spring blade. The heavy member comprises a set of masses that is movable in translation in said casing along a longitudinal direction. A wormscrew driven by drive means is engaged in a slider nut of said set of masses. The set of masses comprises two masses that are slidable respectively in two cylindrical spaces of the casing. Each mass presents at least two presser means interposed between the mass and the casing, each presser means comprising a groove formed in a circumference of a mass, each presser means comprising at least one resilient member arranged in said groove and a split ring pressed against the casing by said at least one resilient member of the presser means.

Abstract: The present invention provides methods and apparatus for unmanned aerial vehicles (UAVs) with improved reliability. According to one aspect of the invention, interference experienced by onboard sensors from onboard electrical components is reduced. According to another aspect of the invention, user-configuration or assembly of electrical components is minimized to reduce user errors.

Abstract: A beam for a rotorcraft rotor and particularly to a helicopter rotor. Said beam comprises a hub connection portion, a blade connection portion, a first flexure portion located between the hub connection portion and the blade connection portion and having a bending stiffness about a first axis which is orthogonal to the longitudinal axis of the blade, said bending stiffness being smaller than that of the hub connection portion and that of the blade connection portion and a shear portion located between the hub connection portion and the blade connection portion and having a shear stiffness parallel to a second axis which is orthogonal to the longitudinal axis of the blade and non-parallel to the first axis. Said shear stiffness is smaller than that of the hub connection portion and that of the blade connection portion.

Abstract: A pin configured for use in a rotor blade movable between an aligned position and a folded position and having a rotor blade airfoil contour is provided including a cylindrical body configured to couple a first section and a second section of the rotor blade when the rotor blade is in the aligned position. A handle is mounted to an end of the cylindrical body and has an airfoil contour complementary to the rotor blade airfoil contour. The handle is movable between an open position and a closed position. When the handle is in the closed position, the handle is flush with an adjacent portion of the rotor blade. When the handle is in the open position, the handle is accessible to pull the cylindrical body from the first and second section s of the rotor blade.

Abstract: A modular Unmanned Aerial System (UAS) includes an Unmanned Aerial Vehicle (UAV) parent module and UAV child modules. A main wing extends from a respective fuselage of the modules. The UAS includes docking mechanisms coupled to wingtips of the main wings. The child modules dock with the wingtips of the parent or an adjacent child module. Docking forms a linked-flight configuration, with undocking and separation from the parent or adjacent child module achieving an independent-flight configuration. The modules have booms arranged transverse to the main wings and parallel to the longitudinal axis, as well as front and rear rotors/propellers. The front and rear propellers have axes of rotation that are normal to a plane of the longitudinal axis in a vertical takeoff and landing (VTOL) configuration, with the axis of rotation of the rear propellers parallel to the longitudinal axis in a forward-flight configuration.

Abstract: A method for three-dimensional (3D) coverage mapping of a coverage area of a cell site using an Unmanned Aerial Vehicle (UAV) includes causing the UAV to fly about the coverage area at one or more elevations; causing the UAV to take measurements of wireless performance during flight about the coverage area; and utilizing the measurements to derive a 3D coverage map of the coverage area.

Abstract: Systems and methods are disclosed for determining a position of a camera affixed to a UAV in flight when the camera captures a digital aerial image. In particular, in one or more embodiments, the disclosed systems and methods utilize real time kinematic satellite navigation techniques to identify a position of a UAV. Moreover, the disclosed systems and methods precisely determine the time that a camera captures a digital aerial image together with an attitude of the UAV at the time of capture to calculate a location of a camera at the time of capture. In one or more embodiments, the disclosed systems and methods can utilize the determined position of the camera together with the captured digital aerial image to generate a three-dimensional representation of a site.

Abstract: A method and system utilizing one or more agricultural drones in combination with agricultural equipment, e.g., an agricultural boom sprayer, to evaluate the crops being farmed, and to improve the real-time delivery and dispensing of liquid from the sprayer including monitoring and verifying that the liquid is being dispensed correctly and/or in accordance with a desired distribution pattern or level.

Abstract: A draining device for draining a fluid line is provided. The draining device comprises a mechanically non-locking coupling and a holding device. The mechanically non-locking coupling is configured to establish a fluid conductive connection with the fluid line. The holding device is configured to stationary fix the mechanically non-locking coupling relatively to the fluid line. The draining device allows establishing a fluid conductive connection between the fluid line and the mechanically non-locking coupling without requiring a mechanical fixation directly at the mechanically non-locking coupling.

Abstract: A seat pan assembly including spaced left and right seat spreaders and a seat cushion assembly supported on the spaced left and right spreaders, the seat cushion assembly including a spring assembly incorporated within at least one layer of seat foam. A seat cushion assembly including at least one layer of seat foam and a spring assembly having a plurality of springs incorporated into the at least one layer of seat foam such that portions of the at least one layer of seat foam are positioned both above and below the plurality of springs.

Abstract: A module for an aircraft cabin and an aircraft with a passenger cabin and such a module where the module includes a door to open the module, and a seat that is fastened to the door. The seat can be a vehicle attendant seat, and the module can be a lavatory. The rear side of the module can nestle against the pressure bulkhead in the tail of the aircraft. The module can include another module directly adjacent to its side, e.g., a galley module.

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

Abstract: An inflatable evacuation device may comprise a ramp portion and a slide portion extending from the ramp portion. A releasable support strap may be coupled between the ramp portion and the slide portion. A release assembly may be coupled to the releasable support strap. The release assembly may be configured to release a tension in the releasable support strap between the ramp portion and the slide portion.

Abstract: An electrical propulsion system for a vehicle. The electrical propulsion system includes at least one generator. The electrical propulsion system also includes at least one drive engine coupled to the at least one generator. The electrical propulsion system further includes at least one electrical device and at least one battery integrated power converter (BIC). The at least one generator and at least one of the at least one BIC and the at least one electrical device are coupled. The at least one BIC and the at least one electrical device are coupled.

Abstract: An aircraft engine assembly including a set of rear engine attachments comprising a first shackle hinged on a bracket secured to the engine and on a bracket made as one piece with one of the two side panels, the shackle being oriented along a vertical direction, a second shackle hinged on a bracket secured to the engine and on a bracket made as one piece with the other one of the two side panels, the second shackle being oriented along the vertical direction, and a third shackle for transversally transmitting loads, inclined relative to the vertical direction and hinged on a bracket secured to the engine and on a bracket secured to the primary structure.

Abstract: A liquid storage tank, for example an aircraft fuel tank, having a tank wall enclosing a liquid storage space, and a tie assembly located at least partially within the liquid storage space. The tie assembly includes an elongate member, for example a wire or cable, and a plurality of attachment devices fixed to an inner surface of the tank wall. The elongate member includes a plurality of spaced part points along its length, each of the spaced apart points being fixed to a respective attachment device such that the tie assembly resists outward deformation of the tank wall.

Abstract: An avionics display for rotorcraft provides a depiction of 360 degrees of terrain and obstacles about the rotorcraft using a top plan view at above a predetermined altitude that transitions to an angle perspective view as the altitude drops. The display provides improved situational awareness for highly mobile aircraft at critical times of takeoff and landing.

Abstract: A pressure bulkhead may include a bulkhead wall having a radially inner disk and a radially outer compression ring, the outer compression ring being reinforced to balance meridional and hoop stresses sustained by the bulkhead wall in response to a pressure differential across the pressure bulkhead; and the radially inner disk being unitary with the outer compression ring and being made of the same material as the outer compression ring.

Abstract: A dynamic exterior aircraft light unit, mounted to an aircraft for illuminating an aircraft environment, includes an LED group with a plurality of LEDs, and an optical system with at least one optical element. The optical system being associated with the LED group for shaping an output light intensity distribution from the light emitted by the LED group and the LED group and the optical system are stationary within the dynamic exterior aircraft light unit.

Abstract: An imaging device can be mounted on a vehicle and used to capture images. The imaging device can include a camera assembly rotatable relative to a platform of the vehicle and about two or three camera axes. The camera assembly can include a camera and a mirror attached to the camera. The mirror can be rotatable relative to the camera and about one or two mirror axes, different from the camera axes. Users can provide input to controllers that operate the vehicle, the camera, and the mirror to control both flight and the line-of-sight of the camera. The controllers combine separate inputs as well as measured conditions, such as inertial angles, to coordinate control of vehicle, camera, and mirror parameters, such as yaw adjustments to both the camera and the mirror to achieve a desired line-of-sight.

Abstract: In one possible embodiment, a UAV payload module retraction mechanism is provided including a payload pivotally attached to a housing. A biasing member is mounted to bias the payload out of the housing and a winch is attached to the payload. An elongated flexible drawing member is coupled between the housing and the winch, the elongated drawing flexible member being capable of being drawn by the winch to retract the payload within the housing.

Abstract: An elastically deployable panel structure for space solar array applications includes a support structure having a first stowed configuration and a second deployed configuration. The stowed configuration has elastic strain energy that powers deployment of the support structure. The elastically deployable panel structure does not include a boom. Longitudinal edges of the support structure may be curved downward to form an open cylinder when in the deployed configuration. The support structure is configured to be operable as a mounting surface for solar cell arrays.

Abstract: Exemplary deployable sheet material systems may be configured to stow and deploy sheet material. The systems may include one or more masts, one or more extendable booms, and one or more guys wires configured to function in conjunction with each other to deploy the sheet material and then to maintain the sheet material in the deployed configuration.

Abstract: A system for controlling a distribution of propellant in a propellant tank assembly for a spacecraft comprises a body for containing the propellant, a plurality of thermal tomography elements, including a plurality of temperature-control elements and a plurality of temperature sensors, disposed around the body for detecting the distribution of the propellant inside the body; and a tomography element control module arranged to control the plurality of temperature-control elements to redistribute the propellant inside the propellant tank body by heating and/or cooling the propellant. In an embodiment, the propellant tank body includes a propellant management device inside the body and the tomography elements are disposed in proximity to the propellant management device. Tomography data can be obtained from the plurality of tomography elements, and a distribution of propellant within the propellant tank body can be determined based on the obtained tomography data.

Abstract: A space flight simulator includes: a celestial-body-position output unit configured to output three-dimensional positions of extragalactic celestial bodies in space; an observation-position designation unit configured to allow an operator to designate a three-dimensional position and a posture of an observer in extragalactic space; a celestial-body-image arrangement unit configured to determine, based on the output from the celestial-body-position output unit, arrangement of an image of each extragalactic celestial body in a star field seen from the designated three-dimensional position and posture of the observer, and generate a star field image; a cosmic-expansion selection unit configured to allow the operator to perform selection as to whether a cosmic expansion effect is taken into account; a time designation unit configured to designate an observation time; and a cosmic-expansion correction unit configured to correct the three-dimensional position of each extragalactic celestial body based on the cosmic

Abstract: A process for the manufacturing and filling of plastic containers, the process comprising the steps of: positioning a preform with relation to a mold assembly of two or more components, the preform generally being fabricated from a plastic and being provided with a longitudinal axis and presenting a stretchable portion and a non-stretchable portion; stretching the preform along its longitudinal axis; injecting a fluid into the interior volume of the preform, the fluid being under such pressure as to cause the preform to plastically deform until achieving the desired size and shape; and releasing the container from the mold assembly and sealing the container, and in which at least a portion of the stretchable portion of the perform is at a temperature below its vitreous transition temperature (Tg) and, preferably, at ambient temperatures.