Abstract: To provide a brake controller and a brake system that appropriately brake a rotary body of a human-powered vehicle, a brake controller includes one or more processors configured to programmatically control a braking portion of a brake device so that the braking portion brakes a rotary body of the human-powered vehicle based on first information related to travel of the human-powered vehicle, the first information excluding a road surface gradient.

Abstract: A novel cycle device including a transmission assembly (or assemblies) that significantly reduces torque interference with steering operations is provided. Such an assembly is provided in one or more of a modular, fixed or movable configuration according reduced complexity of implementation, improved efficiency of operation, and useful assembly modularity for manufacture and repair. Such a device may further include an improved means for selecting between direct and overdrive functions of a fixed transmission assembly. Additionally, a removable front transmission assembly comprising a steering fork with handlebars is also encompassed herein.

Abstract: A human-powered vehicle control device includes an electronic controller operatively coupled to a motor that assists in propulsion of a human-powered vehicle. The electronic controller is configured to changes at least one of a ratio of output of the motor to a human driving force that is input to the human-powered vehicle or an upper limit value of an output torque of the motor in accordance with the human driving force inputted to the human-powered vehicle upon determining a transmission ratio of the human-powered vehicle is in a predetermined range.

Abstract: A human-powered vehicle control device includes an electronic controller operatively coupled to a motor that assists in propulsion of a human-powered vehicle. The controller is configured to control the motor in accordance with a human driving force that is input to the human-powered vehicle and is configured to change responsivity of an output torque of the motor to a change in the human driving force in accordance with a rider's pedaling posture of a rider of the human-powered vehicle. The human-powered vehicle control device is configured to change an output performance of the motor without operation of a switch.

Abstract: A bicycle rear sprocket assembly comprises at least one sprocket and an internal cavity. The at least one sprocket includes at least ten internal spline teeth configured to engage with a bicycle hub assembly. The at least ten internal spline teeth have an internal-spline major diameter. The internal cavity has a maximum outer diameter larger than the internal-spline major diameter.

Abstract: A bicycle chain guide includes a base and a chain guide. The base is configured to be mounted to a bicycle that includes a solitary sprocket having a rotational center axis. The chain guide is disposed above the solitary bicycle sprocket in a mounted state where the base is mounted to the bicycle. The chain guide includes a first guide plate, a second guide plate, and a bridge. The first guide plate has a first guiding surface. The second guide plate is closer to the base than the first guide plate and has a second guiding surface facing the first guiding surface to define a chain guiding slot between the first guiding surface and the second guiding surface. The bridge connects the first guide plate and the second guide plate.

Abstract: A hybrid drive for an electric bicycle comprising a pedal crank drive that contains a pedal crank axle connected to pedal cranks at both ends, an electromotive drive electrically connected to an accumulator, which contains two electric motors that are connected to different transmission elements of a superposition transmission, which on the drive side is connected to the pedal crank drive and on the output side is connected to the sprocket of a chain drive of the electric bicycle recuperative electromotive braking of the electric bicycle with charging of the accumulator.

Abstract: A bicycle operating device includes a base member, first and second cable control bodies, first and second positioning mechanisms, an operating member and an input mechanism. The first positioning mechanism selectively maintains the first cable control body in a first predetermined position. The second positioning mechanism selectively maintains the second cable control body in a second predetermined position. The input mechanism moves the first and second cable control bodies between the first and second predetermined positions in accordance with a predetermined operation sequence having a changing point to change operation from the first cable control body to the second cable control body. The input mechanism moves the first cable control body by at least two of the first predetermined positions in a single continuous operation of the operating member. The input mechanism includes a restricting structure that prohibits movement of the first cable control body at the changing point.

Abstract: An Extendable/Retractable Shade Apparatus for attachment to a boat tower or boat top or boat cargo rack.

Abstract: A float for a barrier for a waterway, a waterway barrier including the float, and a method for forming the waterway barrier are provided. The float includes a caseless float body which is formed of a single, homogeneous material. The material may be a high density urethane or a functional equivalent.

Abstract: There is provided a method of arranging a vessel assembly including first and second vessels interconnected via a flexible conduit for transferring matter between the first and second vessels, a first end of the conduit in fluid communication with a first manifold of the first vessel, and a second end of the conduit in fluid communication with a second manifold of the second vessel.

Abstract: It relates to an urban craft, which belongs to the industrial sector of nautical vehicles for transportation of crew and passengers in general, composed of a speedboat (1) equipped with a central cab (2), a transparent roof (3), a honeycomb grid (4), an X-shaped structure (5), faceted areas (6), a catamaran hull (7), an inverted nose (8), a negative bow (9), engines (10), a propeller (11), seats (12), safety belts, airbags, acceleration and braking pedals (13), a steering wheel (14), a dashboard (15), a central console (16), a gear shift lever (17), armrests (18), cupholders (19), internet/Wi-Fi access, detachable tablets (20), a lateral boarding platform (21), headlights (22) and lateral arrows in the camera-based rearview mirrors (23), an air-conditioning system, a pneumatic suspension system with adjustable airbags and hydrogen-based shock absorbers, individual (rear and front) lateral doors (24), large gullwing lateral doors (25), an upper airfoil (26), a rear window (27), a foldable rear platform (28) wi

Abstract: A fin system for releasibly securing a fin to a water craft the system including: a fin box with at least one elongated slot open at a first surface of the fin box and extending a depth inward towards a closed base opposite the first surface; one or more fixed securing features in the fin box, below the first surface and adjacent and open to the at least one elongated slot; one or more vertical access slots in the fin box, open at one end to the first surface, adjacent and open to the at least one elongated slot and extending the depth inwards towards the closed base; and, a fin with a fin base dimensioned to be slideably received by the at least one elongated slot of the fin box, wherein the fin base includes one or more fixed fin attachment mechanisms each having at least one tab or recess dimensioned to be received first by the one or more vertical access slots and received subsequently by the fixed securing features, wherein an engagement of the at least one fin tab or fin recess with the securing feature

Abstract: Disclosed is an apparatus, optionally mounted on a stand up paddle board, or surfboard, to lift the board above the water surface and support the board in a stable position above the water surface while a rider standing on the board and maintaining a speed in the water via paddling. In one embodiment, the apparatus includes a strut; a fuselage connected to said strut; a back foil portion connected to an aft end of said fuselage wherein the back foil portion includes two back wings extending outwardly from said aft end of said fuselage; and a forward foil portion connected to a fore end of said fuselage wherein the forward foil portion includes two front wings extending outwardly from said fore end of said fuselage and wherein the forward foil portion has a maximum thickness located at first distance from the fore edge of the forward foil portion.

Abstract: A floating wind turbine assembly, configured to self-stabilize in water without a fixed anchor. The floating wind turbine assembly has a wind turbine, joined to a turbine shaft. A beam anchor is joined to the turbine shaft. A hollow moving mass, arranged around the beam anchor, such that the hollow moving mass can be moved up or down the beam anchor. The hollow moving mass includes a pump, having a pump first end connected to the water with a first pump hose and a pump second end arranged within the hollow moving mass with a second pump hose.

Abstract: Systems and methods directed to marine fenders include fender rotation through a vertical plane while translating horizontally. Fenders are extended and retracted radially outwardly from and radially inwardly to a marine vessel by at least one electrically or pneumatically controlled and/or operational linear actuator. If a plurality of fenders are provided on a starboard and/or port side of the marine vessel, all of the plurality on a particular side may be activated substantially contemporaneously by control from the helm of the marine vessel, such as a recreational pontoon boat.

Abstract: The present disclosure relates to sea floor mapping, and more particularly to a method, system, and apparatus for mapping a large swath of sea floor at substantial depths. An example autonomous underwater vehicle may include: a controller; a body having a front end and a rear end and defining a cavity and a center of gravity; a first dive plane extending from the body proximate the center of gravity; a second dive plane extending from the body substantially opposite of the first dive plane proximate the center of gravity; a counterweight disposed within the cavity configured to be moved between the front end and the rear end of the body, wherein a fore-aft pitch of the body of the autonomous underwater vehicle is controlled by the controller through movement of the counterweight toward the front end or the rear end of the body.

Abstract: Disclosed herein is an inventive dual propeller assembly that can be manually or automatively assembled and includes a leading propeller, and a trailing propeller which are coaxially aligned and secured with a propeller shaft and a locking nut. Various embodiments are disclosed with and without interior grooves for alignment. In all embodiments, the two propellers are secured and aligned with a propeller shaft and locking nut assembly.

Abstract: A semiconductor device includes a semiconductor substrate, a device layer over the semiconductor substrate, a first color filter in a top surface of the device layer and adjacent to an edge of the device layer, and a second color filter in the top surface of the device layer. The second color filter has substantially the same thickness and the same color as the first color filter.

Abstract: A high altitude or stratospheric balloon system may include a balloon envelope including envelope film, at least one tendon, and a suspender. The suspender may have a first end attached to the envelope film. The suspender is arranged to stretch such that the first end moves towards an equator of the balloon envelope as the balloon envelope pressurizes in order to control movement of the envelope film relative to the tendon and towards the equator as the balloon pressurizes.

Abstract: A pole-shaped aircraft framework assembly including a first plug-and-turn connector forming a first end, a second plug-and-turn connector forming a second end, the second end opposite the first end, a first rod extending from the first plug-and-turn connector towards the second plug-and-turn connector, and a coupling component coupled to the second plug-and-turn connector for detachable coupling with the first rod. The first rod has a circumferential outer surface including alternately on a circumferential path in a cross-sectional plane of the first rod a ridged section and a plain section. The coupling component includes a tubular part having a circumferential inner surface including alternately on a circumferential path in a cross-sectional plane of the tubular part at least one ridged section and at least one plain section. One of the first rod and the coupling component is rotatable relative to the other one, engaging respective ridges of the first rod and the coupling component.

Abstract: Devices and methods to capture moisture at a structural member in a vehicle. The devices include a flexible tray that can snap-fit onto an exterior of the structural member. Once attached, the flexible tray can collect moisture from the structural member. A diverter is coupled to the flexible tray. The diverter diverts the collected moisture away from the structural member.

Abstract: A planar pressure bulkhead for an air- or spacecraft, including a first planar wall designed as a pressure seal for a fuselage structure, a second planar wall arranged opposite the first wall, and a reinforcing structure which is arranged between the first and the second wall and which includes at least one circumferential monolithic reinforcing element. Furthermore, the present disclosure provides an air- or spacecraft, including a fuselage structure and a planar pressure bulkhead that is coupled to the fuselage structure in a circumferentially continuous manner.

Abstract: An access cover for an aircraft hole that comprises a plurality of access cover holes, an inner surface, a plurality of first projections protruding from the inner surface, and a plurality of fixing elements configured to fix the access cover to a supporting structure of the aircraft hole. The fixing elements each comprise a male fixing element having an outer threaded surface, the male fixing element being configured to pass through a hole, and a locking element comprising a threaded hole and an extended portion, wherein the outer threaded surface of the male fixing element is configured to thread with the threaded hole of the locking element.

Abstract: Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

Abstract: A wing segment for an aircraft includes a first skin element with a material having anisotropic characteristics and a rib element arranged between leading and trailing edges of the wing segment. The first skin element is attached to the rib element such that deformation of the skin element results in a twist of the wing segment with respect to a main extension direction of the wing segment. The wing segment further includes a control unit to control deformation of the skin element in order to adjust the twist of the wing segment to achieve a predetermined twist of the wing segment.

Abstract: A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.

Abstract: The invention relates to a rotating front part of an aircraft turbomachine intake comprising bolts for attaching a cone tip to an internal support, each bolt comprising a rear end that is screwed into the support and a front end that receives a clamping nut, a rotation-prevention portion of non-circular cross section of each bolt engaging with a hole of corresponding cross section of a rotation-prevention ring. Also provided are extraction bolts, of which a rear end is screwed into the filling piece, each bolt passing through a cone tip flange. Finally, the invention is configured such that, after removal of the nuts, forward tension on the bolts allows the removal of an assembly comprising the tip and the filling piece, while keeping the bolts screwed to the support.

Abstract: There is provided a control stick module (10) comprising: a first shaft (100); a second shaft (110); a joint (140) connecting the first and second shafts; and a gimbal mechanism (120); wherein the joint is nested within the gimbal mechanism. The gimbal mechanism provides axes of rotation (201, 202) for the first shaft (100) and the joint provides axes of rotation (203, 204, 205) for the first shaft (100); and the axes of rotation (201, 202) provided by the gimbal mechanism intersect at a point corresponding to a point of intersection of the axes (203, 204, 205) provided by the joint.

Abstract: A carriage for supporting and guiding an aircraft flap translationally moveable along a linear slide bearing comprises a drive element connectable to an actuator for receiving a translational actuating force causing a translation of the carriage along the slide bearing. A flap support of the carriage is configured to, upon translational movement of the carriage, transmit the actuating force to the flap. The carriage further has a slide plate with at least two slide elements arranged on opposed sides of the slide plate which are engageable to at least two corresponding linear slide rails of the slide bearing.

Abstract: A flap actuating system for use in an aircraft comprises a carriage for supporting and guiding a flap which is engageable with and translationally movable along at least one linear bearing rail. A linear actuator of the flap actuating system has a linearly actuatable coupling element coupled to the carriage and a drive element configured to linearly actuate the coupling element in a direction substantially parallel to a movement direction of the carriage along the linear bearing rail. The drive element is arranged substantially parallel to the movement direction of the carriage along the linear bearing rail.

Abstract: Systems for compensating for force fighting in multi-actuator systems are provided. A drive controller unit comprises a first feedforward controller in communication with a first actuator and configured to receive a drive command signal. A first feedback regulator is configured to output a first feedback input into the first feedforward controller, and to receive as input a first actuator position and a first actuator force. The drive controller unit further comprises a second feedforward controller in communication with a second actuator and configured to receive the drive command signal. A second feedback regulator is configured to output a second feedback input into the second feedforward controller, and to receive as input a second actuator position and a second actuator force. The drive controller unit utilizes both feedforward controllers and both feedback regulators to minimize force fighting while driving a common aileron.

Abstract: A high-integrity, redundant flight control system includes a plurality of flight control computers each having a back-up inertial sensor embedded therein. At least one back-up inertial sensor provides a respective back-up signal to at least one of the flight control computers. The system includes a plurality of primary inertial sensors discrete from the flight control computers. Each primary inertial sensor is operatively connected to at least one respective flight control computer. Each inertial sensor provides a respective primary signal to its respective flight control computer.

Abstract: An aircraft control system includes a flow control device and a control circuit. The flow control device is configured to control a flow of air around an aircraft. The control circuit is configured to control the flow control device so that a pressure distribution loaded on a surface of a structure that constitutes the aircraft is equal to a control value of a pressure distribution calculated based on a physical quantity detected by a sensor provided in the aircraft. The physical quantity relates to the air.

Abstract: An unmanned aerial vehicle (UAV) includes a central body and a plurality of landing gears that are extendable from and movable relative to the central body. The plurality of landing gears are configured to transform between a flight configuration and a surface configuration. In the flight configuration, the landing gears are extending laterally away from the central body and not in contact with a surface below the central body. In the surface configuration, the landing gears are extending towards the surface below the central body. When the landing gears are in the surface configuration, the landing gears are configured to support a weight of the central body on the surface and transport the UAV over the surface by moving one or more of the landing gears relative to the surface.

Abstract: The invention relates to an aircraft undercarriage provided at its bottom end with a rocker arm (2) carrying at least two axles (4, 5), including one in front of a hinge between the rocker arm and the undercarriage and the other behind said hinge. According to the invention, one of the axles is fitted with one or more braked wheels (6) and the other axle is fitted with one or more motor-driven wheels (8).

Abstract: A piston for use in a liquid inertia vibration elimination (“LIVE”) system. The piston includes a port that extends from a first end of the piston to an opposite second end of the piston, wherein a length of the port is longer than a length between the first and second ends of the piston.

Abstract: Systems and methods for cueing a helicopter pilot when a flight parameter (such as rotor-induced vibration level, airspeed, bank angle, icing accumulation, etc.) exceeds operational constraints. This is accomplished by reformulating the on-board cockpit active vibration control system to add a pilot cueing aid. When the measured flight parameter becomes excessive, the active vibration control system is temporarily detuned, which reduces the amount of vibration suppression it provides or turns off vibration suppression, causing an increase in airframe vibration levels to cue the pilot to take action (e.g., to fly within operating limits).

Abstract: A compound aircraft embodies an array of rotors for vertical flight positioned on support booms and wing elements for cruise flight coupled to a central fuselage housing avionics and a pusher propeller for forward propulsion. The aircraft accommodates a cargo-carrying container with mating of the surfaces between container and fuselage and latching mechanisms for attaching and detaching the container and vehicle.

Abstract: A helicopter includes a rotor system having a rotor with an adjustable pitch that is controlled at least in part by a pilot using a collective control and which helicopter generates a Low RPM signal that is indicative of a threshold low rotational speed of the rotor. An actuator arrangement can move the collective control by exerting a force on the collective control such that the pilot is able to overcome the actuator force but which otherwise can move the collective control from a current operational position toward a minimum pitch position. A clutch can co-rotate with a motor to serve in transferring the actuation force to reduce the adjustable pitch and can slip relative to the actuator shaft assembly responsive to an application of a counterforce applied by the pilot to the collective control such that the counterforce overcomes the actuation force.

Abstract: A device for controlling a collective pitch and a cyclic pitch of rotor blades of a rotoreraft of a direct turbine driven type and. contra-rotating coaxial rotor type (DTDR) includes: a lower rotor and an upper rotor that are mounted concentrically on a shared rotor shaft; a first plate, that is not rotatable, fastened to a structure of the rotorcraft and connected to an actuator that communicates collective pitch and cyclic pitch controls to it, the first plate being mounted so as to be movable in translation along the shared rotor shaft and to oscillate relative to the shared rotor shaft, via a lower ball joint mechanism; and a second plate, that is rotatable, housed on the lower bail joint mechanism so as to be always parallel to the first plate, the second plate being driven in rotation by a member connecting it to the lower rotor.

Abstract: There is provided a rotorcraft, including a body, including a front portion and a tail portion; a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body; and an anti-torque system coupled to the tail portion of the body, the anti-torque system including a primary tail rotor system and a secondary tail rotor system; wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force. In other aspects, there are methods of providing anti-torque force in a rotorcraft.

Abstract: Method and apparatus for a flight vehicle including a wing having a high aspect ratio and first and second rotors having a high aspect ratio, with a ratio of the rotor diameter to wing length ratio is equal to or greater than about 0.25. In embodiments, the flight vehicle can include a first and second motor, each less than about one thousand HP, to drive a respective rotor and a second motor. The flight vehicle can include a cruise mode and a VTOL mode.

Abstract: An aircraft includes a tiltwing where the tiltwing is a single wing to which starboard-side and non-foldable outer propeller, a port-side and non-foldable outer propeller, a starboard-side and foldable inner propeller, and a port-side and foldable inner propeller are coupled to. Those rotors rotate at least some of the time when the tiltwing is in a vertical takeoff and landing position. The starboard-side and foldable inner propeller and the port-side and foldable inner propeller are stowed at least some of the time when the tiltwing is in a forward flight position. The tiltwing rotates about an axis of rotation, when rotating between the vertical takeoff and landing position and the forward flight position, that is higher than the aircraft's center of mass.

Abstract: This aircraft without wings is designed to allow unmanned flight to any place on earth by simplified construction. This is accomplished by turning the gas turbine engine upward, by means of a geodesic flight organizer, by air mass cooling, and because of its massive amount of power. The VTOL aircraft is never detained by looking for a runway. A conventional jet aircraft needs a long runway to go fast enough for takeoff speed. That's why airports are so big, because conventional jet planes sometimes have to take off at 200 miles per hour for lift. This aircraft shoots straight upwards and then the horizontal stabilizers are turned on. The small-sized box or barrel goes anywhere you want it to go. The aircraft is designed to allow unmanned flight to any place that has air, or the gas of another planet. The aircraft is guided by using a geodesic flight organizer and a gyro. The air mass is split so part goes to the combustion chamber and the other part goes to the thruster for oxygen power.

Abstract: A three-dimensionally scalable, modular and customizable aircraft composed of stably flyable plurality of planar unitary systems which provides a coordinated thrusting vector in any direction of the three-dimensional space. The aircraft includes at least one circumferential frame that surrounds the system in one plane that houses at least one rotatable piece that allows the system to rotate around at least one rotation axis relative to the circumferential frame. The aircraft includes at least two assembly regions located on the external surfaces of the circumferential frame which is used to attach at least two adjacent modules by touching each other, and also includes at least two electrical power transmission regions that are aligned with the corresponding identical region of the next module which allows sharing of the power sources providing energy to the system among all of the modules.

Abstract: A painting system that makes use of drones such as modified quadrotors. The drone includes a support arm that carries a paint nozzle configured for pan and tilt motion. A power supply line is connected from an external power supply to the drone to allow extended flight time. A paint supply line is also connected from an external paint supply to the drone to allow extended painting time and/or surface coverage with each flight. The drone has an onboard controller so painting is autonomous with no human input being required. The drone stores a 3D model of the target structure annotated with the drone trajectory plus commands to control the pan-tilt paint nozzle to perform the painting. At runtime, the controller uses a sensor to view the target structure and localizes itself. The drone then traverses the stored trajectory and implements the painting commands to paint the 3D structure's surfaces.

Abstract: A bladeless unmanned aerial vehicle includes a body and two or more thruster assemblies coupled to the body. The thruster assemblies each includes a ducted fan compressor and a discharge frame. The discharge frames may be bladeless fans or may be nozzles. The discharge frames may be positioned substantially vertically, tilted at an angle about an axis extending radially from the center of the body, and/or angled in a vertical plane aligned with an axis extending radially from the center of the body.

Abstract: A remote-controlled unmanned foldable aircraft comprises at least two motors that allow the aircraft to fly, and at least one support structure for supporting said motors; the support structure is flexible and inflatable such that the support structure can be folded and unfolded between a storage position and an operational position.

Abstract: Autonomous aerial vehicles and methods of operating the same. An unmanned aerial vehicle in accordance with various embodiments may receive a defined flight path, at least a portion of which is underground. The vehicle may then autonomously travel along the defined flight path and gather imagery regarding its environment as it travels.