Abstract: A vehicle height adjustment device includes a rear suspension, an electromagnetic valve control unit, and a weight estimation unit. The rear suspension includes a support member. The electromagnetic valve control unit determines a target movement based on an interrelation between the target movement and a weight applied to a vehicle, under which the target movement is set to an upper limit when the weight is larger than a predetermined weight, so that an actual movement of the support member reaches the target movement. The electromagnetic valve control unit determines the target movement based on a temporary weight. The weight estimation unit increases the temporary weight, even when the actual movement reached the target movement. The electromagnetic valve control unit decreases the target length, even when the temporary weight increased. The weight estimation unit estimates as the weight the temporary weight when the actual length has finally reached the target length.

Abstract: A motorized self-balancing vehicle is provided. The vehicle may include at least two wheels. The vehicle may include a self-balancing mechanism. The vehicle may include a manual-drive mechanism. The self-balancing mechanism may constantly update the self-balancing vehicle in order to maintain the balance of a rider of the vehicle, while the rider is engaged in human motion on the manual-drive mechanism. The human motion may include pedaling and/or stepping. The vehicle may include an electric motor. The vehicle may include only an electric motor. The vehicle may include only a manual-drive mechanism. The vehicle may include both the manual-drive mechanism and the electric motor. In the embodiment including the manual-drive mechanism and the electric motor, the power generated by the electronic motor may be combined with power generated by the manual-drive mechanism in order to move the vehicle.

Abstract: This disclosure generally relates to an electric vehicle. More specifically, this disclosure describes a motor control system for an electric vehicle that activates and deactivates a hill hold assist mode and a hill start assist mode for the electric vehicle. The hill hold assist mode is used to help ensure the electric vehicle remains stationary while stopped on an uphill incline. Likewise, the hill start assist mode is used to help a rider of the electric vehicle start the electric vehicle moving again once it is stopped on the uphill slope.

Abstract: A bottom bracket is connected to a spindle and a frame of a bicycle. The bottom bracket comprises a housing and an adapter. The housing is connected to the frame and comprises a substantially circular disc, one or more pins, and an actuating mechanism. The disc comprises a plurality of disc openings arranged proximate to a circumferential edge of the disc and is adapted to rotate with the spindle. The pins selectively engage with the disc openings, wherein the engagement of the pins with the disc openings prevents further rotation of the disc. The actuating mechanism selectively engages the pins with the disc openings. The adapter removably is attached to the housing and connected to the frame.

Abstract: A drive train for a human-powered vehicle comprises a drive unit, a sprocket arrangement, and a total gear range quotient. The drive unit includes a motor configured to impart propulsion to the human-powered vehicle. The sprocket arrangement is operatively coupled to the drive unit. The sprocket arrangement comprises a plurality of rear sprockets and a plurality of gear ratios respectively corresponding to the plurality of rear sprockets. The plurality of gear ratios includes a largest gear ratio and a smallest gear ratio. The total gear range quotient is obtained by dividing the largest gear ratio by the smallest gear ratio. The total gear range quotient is larger than 5.

Abstract: A bicycle electric derailleur making use of a geared electrical motor located on the predominantly stationary portion of said derailleur assembly thereby alleviating extraneous loads to actuating apparatus due to inherent shocks and vibrations, and additionally offering suitability for implementation in an automatic electronic control system as well as simpler manual apparatuses through reliance on a variety of versatile derailleur position resolving means for superior adaptability.

Abstract: A method for determining a displacement of an anchor is provided. The method includes the steps of: determining an initial position of the anchor; and determining a displacement of the anchor. The step of determining the displacement of the anchor includes (i) measuring anchor velocity values, (ii) measuring at least one further physical quantity associated with the anchoring, (iii) deciding whether the anchor is at rest or in motion, wherein a value of the further physical quantity is taken into account in the decision, and (iv) integrating the velocity values over time during intervals when the anchor is deemed to be in motion.

Abstract: An electronically powered, light emitting fin used with a surfboard or paddleboard, or similar water sports board. The fin is configured to be attached to the water sports board to provide illumination under the board when using the device. The lighted fin may be particularly useful when using the water sports board at night to illuminate water beneath the board.

Abstract: Disclosed herein is a towline guard device which prevents a towline attached to a wakeboard tower of a boat from catching while pulling a rider. The device includes a coupling located at the distal end of the device. The device further includes a boom assembly connected to the coupling. The coupling further provides a first joint which allows the boom assembly to move in a first axis. The boom assembly may comprise one or more elongated members and one or more towline guides.

Abstract: We have invented a floating platform with 3 canted columns, a new type of fairlead, and a new method of mooring line makeup and installation method, that can be used for canted columns. The platform includes 3 columns having upper ends projecting above water surface. The columns are canted or inclined inward from the corner of hull toward the central vertical axis. The 3 columns converge at the top of column such that each column will lean against the other 2 columns. Each column has two connection points to the other 2 columns. Horizontally disposed pontoons interconnect adjacent columns at the lower ends. The columns and pontoons form a closed structure hull to support a foundation structure directly above the top of column.

Abstract: An item of equipment for producing a floating photovoltaic installation, of modular design, which includes float modules constituted, in whole or in part, of plastic casings, confining an air volume, having a neck with an opening, blocked by a stopper, structural modules, support elements, and possibly, connecting modules. The structural modules and/or the connecting modules include lugs intended to face one another for the assembly of the modules, and wherein the float modules are configured such that the assembly of the lugs facing one another is obtained, in whole or in part, by inserting the neck through the lugs, the stopper not present, then locking the assembly by the placing of the stopper blocking the opening of the neck.

Abstract: The present invention relates to a spread moored vessel for production and/or storing of hydrocarbons. The vessel comprises a laterally extending main deck, a symmetrical mooring arrangement for mooring the vessel to a seabed when the vessel is floating in a body of water and a longitudinal hull. The longitudinal hull further comprises a bow, a midbody, a stern, and a motion suppressing element protruding out from the longitudinal hull, below the vessel's maximum draught. The ratio between a maximum length (Lw1) and a maximum breadth (Bw1) of the longitudinal hull, at the vessel's maximum draught, is between 1.1 and 1.5. The specific hull shape with the particular length/breadth ratio and the motion suppressing element allows for favorable and uniform motions regarding of wave direction in relation to vessel heading.

Abstract: A damping system is presented for damping an oscillation of a load on a fluctuant water surface. The damping system may include four buoyancy systems, two on each side of the load. Each buoyancy system may include two buoys, a lower frame and an upper frame.

Abstract: The objective of the present disclosure is to provide a collision avoidance assistance system for assisting avoidance of collision between a ship and an obstacle using a result obtained by (i) detecting the obstacle on a ship travel route using sensors, (ii) identifying the detected obstacle, (iii) collecting sensor data, and (iv) analyzing the collected sensor data. By using the system including, as a component, a sensor group, a three dimensional viewing field acquirer, an obstacle identifier, a database regarding obstacles, an analyzer, a deep learning unit, a learning unit, and communicator, the obstacle on the ship travel route is detected and identified, and by using a result obtained by detecting, identifying, collecting, and analyzing sensor data, avoidance of collision between the ship and the obstacle is assisted.

Abstract: An overboard tracking device is an apparatus which facilitates the location of individuals wearing Personal Flotation Devices (PFDs) or similar survival devices in a body of water. The apparatus includes a prismatic buoyant housing, a power source, at least one switch, a controller, a transceiver, a thermionic layer, an antenna layer, and a waterproof casing. The prismatic buoyant housing maintains the apparatus above water. The power source provides power for the operation of the apparatus. The at least one switch enables manual or automatic activation or deactivation for the apparatus. The controller processes the data and signals received from external radar sources. The transceiver facilitates the sending and receiving of radio wave signals to/from external radar sources. The thermionic layer generates the power stored in the power source. The antenna layer transmits radio waves from/to the transceiver. The waterproof casing prevents contact of the electronic components with water.

Abstract: An escape system comprises a slide for facilitating evacuation of from a structure to water, wherein the slide comprises at least one helical inflatable path. The or each helical inflatable path may be configured to extend generally vertically between the structure and the water. The slide may comprise a plurality of helical inflatable paths. The slide may comprise spacing means for controlling the pitch between helix turns of the or each of the helical inflatable paths. A bowsing arrangement for the slide is also disclosed.

Abstract: Methods to build implantable micro-sensors used to detect tissue-dissolved inert gas and to detect microbubble formation to avoid Caisson disease are described. The disclosed methods and devices are based on measuring physical changes in hydrophobic liquids after absorbing an inert gas such as nitrogen. The teachings of the disclosure help improve safety and efficiency of diving operations.

Abstract: This invention relates to a mouthpiece configured for engaging a snorkel or a first and/or second SCUBA diving regulator having at least one internal receiving chamber formed in at least one of the opposing bite wings and configured to receive and retain a fluid or gel therein, whereby an effective amount of the fluid or gel may be selectively introduced through at least one selectively sealable fluid delivery opening formed in one or more of the bite wings and/or formed in a side wall of the internal receiving chamber, whereas upon application of sufficient pressure or force by the teeth of the user, an effective amount of the fluid or gel flows into the user's mouth to overcome or substantially ameliorate the effects associated with salt mouth.

Abstract: A diving mask system is disclosed comprising a faceplate having a lateral partition on an interior surface delineating an upper and lower section, the lower section comprising a region that extends away from the upper section and includes at least one cutout opening fitted with a complementary-shaped flexible insert that enables a user to grasp the nose. The faceplate further includes a snorkel coupling having a passageway contained therein and conduits connecting the passageways with a lower chamber. The faceplate further includes a flexible tubular insert defining a passageway extending through the faceplate to the lower chamber. The tubular insert has a distal end dimensioned to fit and seal onto the mouthpiece receiver tube of a conventional second stage scuba regulator. The mask may be interchangeably configured for both scuba and snorkeling environments.

Abstract: A propeller for a water vehicle is provided, comprising a hub and at least two blades, said blades extending outwards from the hub in the radial direction, and the propeller having a uniform blade distribution. The problem addressed by the invention is to provide a propeller for a water vehicle which allows unwanted generation of noise to be efficiently reduced or avoided. According to the invention, the angular distance between the blade tips of two consecutive blades of the propeller varies in relation to the angular distance between the blade tips of two other consecutive blades.

Abstract: Air stair support systems, stair support cable assemblies, and hooks are disclosed herein. A stair support system includes, but is not limited to, an aircraft fuselage, a door seal, a stair door, and a stair support cable assembly. The aircraft fuselage defines a door frame and a stair hook receptacle. The stair door has a retracted position within the door frame and an extended position that forms an entry/exit stairway. The stair support cable assembly includes a cable and two hooks. The first hook includes a curved end portion configured to hook onto the stair hook receptacle, a cable end portion secured to the cable, and an intermediate portion having first and second intermediate legs that extend the intermediate portion away from the door seal when installed on the door frame and the stair door. The second hook is configured to hook on the stair door.

Abstract: Systems and methods include providing an aircraft with a fuselage having a sliding door system disposed on at least one side of the fuselage. The sliding door system includes a forward sliding door having an upper slide rail and a lower slide rail, a rearward sliding door having an upper slide rail and a lower slide rail, an upper rail coupled to each of the upper slide rail of the forward sliding door and the upper slide rail of the rearward sliding door, a lower rail coupled to each of the lower slide rail of the forward sliding door and the lower slide rail of the rearward sliding door, and a plurality of actuators coupled to each of the upper rail and the lower rail and configured to displace and retract the forward sliding door and the rearward sliding door linearly with respect to the fuselage.

Abstract: A modular windshield has a central component and at least one side component. The central component is constructed of polycarbonate and the at least one side component is constructed of acrylic.

Abstract: A rib can be manufactured comprising two opposing outer skins and a plurality of internal reinforcement members connecting the skins together.

Abstract: An example of an aerial vehicle includes a rudder removably connected to the aerial vehicle by a twist lock mechanism. The twist lock mechanism is biased in a locked position by an elastic member.

Abstract: A control device for an aircraft has a control stick configured to be operated by hand of a user. The control stick is pivotable about a longitudinal axis, a lateral axis, and a yawing axis extending through the control stick. Motion of the stick about the longitudinal axis is configured to cause roll motion of the aircraft, motion of the stick about the lateral axis is configured to cause pitch motion of the aircraft, and motion of the stick about the yawing axis is configured to cause yaw motion of the aircraft. Rotation of a thumbwheel carried by the control stick changes a magnitude of a thrust vector of the aircraft.

Abstract: In an embodiment, a method includes: obtaining a first signal from a first sensor of a rotorcraft, the first signal indicating measured angular velocity around a first axis of the rotorcraft; filtering the first signal with a lag compensator to estimate angular position around the first axis of the rotorcraft; and adjusting flight control devices of the rotorcraft according to the estimated angular position and the measured angular velocity around the first axis of the rotorcraft, thereby changing flight characteristics of the rotorcraft around the first axis of the rotorcraft.

Abstract: A ballistic descent vehicle comprises an airframe, one or more control surfaces for controlling a descent of the vehicle, a controller, and a sensor suite to estimate both relative position, velocity, and flight path angle. Such a controller guides the vehicle, via the control surfaces, based on the estimated vehicle states, and a preprogrammed equivalent airspeed versus flight path angle two dimensional surface. During flight, the controller periodically consults the pre-computed equivalent airspeed versus flight path angle surface to obtain a desired flight path angle such that the vehicle asymptotically approaches a desired terminal approach angle while successfully navigating to the target. The use of this preprogrammed surface allows for the control of such vehicles with significantly lower computational resources, smaller control surfaces, and/or without relative airflow sensors onboard.

Abstract: In one embodiment, a flight control system is configured to receive one or more pilot inputs intended to effect a particular control outcome for the aircraft, receive one or more current flight parameters of the aircraft, determine whether or not the aircraft is near or in a stall, and if it is determined that the aircraft is near or in a stall, automatically control the aircraft's flight control surfaces in an oscillatory manner that increases the sensitivity of the flight control surfaces and achieves the pilot's intended control outcome.

Abstract: A gimbal having a split design, which can be used in an assembly for actuating an aerodynamic high lift device, is described. The gimbal enables a rotating load path when a force is transferred from the actuator to the high lift device via the gimbal. In particular, the split design can include two receivers which can be coupled to posts extending from a nut. The nut can be secured to a shaft which receives a force generated by the actuator. In one embodiment, the actuator can rotate the shaft to cause the gimbal to translate along the shaft.

Abstract: A bracket for connecting a traverse of a landing gear to a cabin of a helicopter. A landing gear retainer is fixed around the traverse coaxially to the longitudinal direction of the traverse and at least one cabin clamp mount is fixed to the cabin. The landing gear retainer is in between the cabin and upper and lower pendulum bolts and upper and lower pendulum bearings. A pendulum is in longitudinal direction of the traverse hinged to the landing gear retainer. The invention is further related to an application of such brackets.

Abstract: An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

Abstract: An inflatable device for aircraft buoyancy, configured to be inflated in case of emergency landing on water, the device comprising a first inflatable chamber configured to be inflated from a source of gas, to change from a folded state to an inflated stated, a plurality of second inflatable chambers, each configured to be supplied from gas flowing in the first chamber, via at least one supply passage, each second inflatable chamber configured to be inflated to change from a folded state to an inflated stated, wherein each supply passage comprises a check valve.

Abstract: An aerial vehicle is provided including rotor units connected to the aerial vehicle, and a control system configured to operate at least one of the rotor units. The rotor unit includes rotor blades, wherein each rotor blade includes a surface area, and wherein an asymmetric parameter is defined, at least in part, by the relationship between the surface areas of the rotor blades. The value of the asymmetric parameter is selected such that the operation of the rotor unit: (i) moves the rotor blades such that each rotor blade produces a respective vortex and (ii) the respective vortices cause the rotor unit to produce a sound output having an energy distribution defined, at least in part, by a set of frequencies, wherein the set of frequencies includes a fundamental frequency, one or more harmonic frequencies, and one or more non-harmonic frequencies having a respective strength greater than a threshold strength.

Abstract: An aircraft that can fly stably when water is discharged from a hose installed on the airframe, and an aircraft system, are provided. The aircraft system can include a master aircraft, slave aircrafts and a remote control device. The aircraft preferably fly as a unit. Each slave aircraft can include four rotary blade portions having propellers, and a suspending means for suspending a part of a hose. The master aircraft may include four first rotary blade portions having first propellers arranged to rotate in a horizontal plane, four second rotary blade portions having second propellers arranged to rotate in a vertical plane, and a nozzle on which a tip end part of the hose is installed. The direction of the center axis of the nozzle is parallel to the direction of the rotational axes of the second propellers.

Abstract: A payload retrieval apparatus including an extending member having an upper end and a lower end, a channel having a first end and a second end, the channel coupled to the extending member, a first tether engager that extends in a first direction from the first end of the channel section, and a payload holder positioned near the second end of the channel and is adapted to secure a payload.

Abstract: Cargo load platform assemblies are especially adapted to provide support for a variety of cargo, such as auxiliary aircraft fuel tanks. According to certain embodiments herein, a load platform is provided which is adapted to being positioned onto a cargo deck of a cargo aircraft. At least one anti-rattle device is operatively associated with the load platform for positionally fixing the load platform to a tie-down ring of the cargo deck of a cargo aircraft. The cargo load platform may support a rigid fuel tank thereon so that auxiliary fuel tankage systems can be provided as may be needed.

Abstract: An entertainment and connectivity system includes a processor for transferring information between a vehicle based user device and a server to validate a user's government identity before granting the user device access to the internet. The vehicle based server has an internet protocol address and communicates with user devices. The user devices each have an onboard internet protocol address mapped to the internet protocol address of the vehicle based server. A processor associated with the vehicle based server receives requests for internet service originating from the user devices. The requests include travel information or internet subscription plan information for a user of each of the user devices. The vehicle based server, or a ground based server that receives the request, generates an internet connection authorization decision based on validation of the user's government identity or the user's internet subscription plan information.

Abstract: The present invention basically relates to an arrangement of individual seats intended to be installed in an aeroplane cabin comprising at least one module of two seats disposed opposite one another, said module having a longitudinal elongation direction, characterized in that said arrangement further comprises: a console disposed between the two seats of the module; a screen connected to each seat, each screen being mounted on a screen support; the screen supports being movable between a stowed position and a deployed operating position, in which the screen supports are positioned substantially edge-to-edge and form a partition wall between the two seats located opposite one another.

Abstract: An aircraft passenger seat including decoupled seat back and seat bottom elements configured to be selectively positioned with respect to spaced seat elements to allow the seat to be used for seating or storage as desired. The passenger seat is convertible by repositioning the seat back and seat bottom elements to provide conventional forward-facing seating, face-to-face seating with a longitudinally aligned and adjacent seat, or seat storage as desired. The seat back and seat bottom elements track along a track assembly affixed along facing inboard sides of fixed seat elements such as arm rest assemblies.

Abstract: An upholstery-guided footrest includes a footrest mechanically coupled to a seat. The footrest is configured for moving between a stowed position and one or more deployed positions. A flexible member has a first end and a second end opposite the first end. The first end is fastened to the seat and the second end is fastened to the footrest such that the flexible member supports the footrest during stowing. The flexible member bends around a frontside of the seat and is configured to guide and support the footrest into a stowed position.

Abstract: Auxiliary power systems, aircraft including the same, and related methods. An auxiliary power system comprises an auxiliary power unit (APU) controller and an APU with an air intake, a powerhead, and a load compressor stage. The load compressor stage includes a flow regulator assembly, a load compressor, and a bleed air temperature (BAT) sensor for generating a BAT signal. The APU controller regulates a flow rate of a load compressor airflow through the load compressor based on the BAT signal. A method of utilizing an auxiliary power system includes compressing a load compressor airflow to generate a bleed air flow, measuring the BAT with a BAT sensor, generating a BAT signal based on the BAT, transmitting the BAT signal to an APU controller, generating a flow regulator command with the APU controller, transmitting the flow regulator command to a flow regulator assembly, and controlling a flow regulator assembly.

Abstract: An aerial vehicle safety apparatus includes an expandable object, an ejection apparatus, a bag-shaped member, and a gas generator. The expandable object is wound or folded in a non-expanded state and generates at least any of lift and buoyancy in an expanded state. The ejection apparatus is coupled to the expandable object by a coupling member and ejects the non-expanded expandable object into air. The bag-shaped member is provided in the expandable object and wound or folded together with or separately from the non-expanded expandable object, and expands the non-expanded expandable object by at least partially being inflated like a tube. The gas generator is provided in the expandable object and inflates the bag-shaped member by causing gas generated at the time of activation to flow into the bag-shaped member.

Abstract: A propulsion system for an aircraft including a fuselage and a wing assembly. The propulsion system includes a first propulsion device at the level of the rear part of the fuselage and constituted of at least one BLI propulsion unit including a fan, a second propulsion device constituted of at least one conventional propulsion unit, and a transmission device coupling the first and second propulsion devices. The second propulsion system therefore generates the energy necessary for driving in rotation the fan of the BLI propulsion unit or units. The thrust produced by the propulsion devices contributes to generating the total thrust of the aircraft. In this propulsion system at least one conventional propulsion unit constituting the second propulsion device is situated on one side of the rear part of the fuselage between the tail of the fuselage and the wing assembly of the aircraft.

Abstract: A rotary propulsion system includes a fan arranged along a rotation axis, an electric motor having windings and a permanent magnet arranged along the rotation axis and operatively connected to the fan, and a reduction gear set. The reduction gear set extends about the rotation axis and couples the electric motor to the fan. The permanent magnet is rotatable relative to the windings and the fan to rotate the fan using the electric motor at a rotational speed that is lower than a rotational speed of the permanent magnet. Aircraft and methods of propelling aircraft are also described.

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises, first, a groove positioned in an extension of the shear pin and, second, a fork connected to the primary structure via at least one removable link and interacting during operation with the groove in such a manner as to immobilize the shear pin in translation.

Abstract: An aircraft engine attachment connecting an attachment body and a primary structure of an aircraft pylon, the engine attachment comprising a shear pin immobilized in translation by a first immobilization system that comprises a shoulder and a removable stop that are integral with the primary structure, between which a flange of the shear pin is immobilized, and a second immobilization system that comprises a stop plate, connected by at least one removable link to the primary structure, which closes the first hole, at least in part.

Abstract: An apparatus and method relating to a generator comprising a housing defining an interior and fluidly separating the interior from surrounding ambient air, at least one of a rotor or stator located within the housing, a cooling circuit passing through at least a portion of the housing to cool the interior and recirculating a coolant having a density greater than the ambient air, and a jet pump having a motive fluid conduit fluidly coupled to the cooling circuit, a transport fluid circuit fluidly coupled to the ambient air.

Abstract: A latch mechanism for use in a ram air turbine actuator including: a coupler housing extending from a first end to a second end opposite the first end, the coupler housing including: a base arm having an upper surface and a lower surface opposite the upper surface; a first wall extending away from the upper surface, the first wall including a first slot; and a second wall extending away from the upper surface, the second wall including a second slot, wherein the upper surface, the first wall, and the second wall at least partially enclose a cavity therebetween; a lock release pivot arm including: a first end; a second end opposite the first end of the lock release pivot arm; an orifice located proximate the second end of the lock release pivot arm; and a pivot pin located within the first slot, the second slot, and the orifice.

Abstract: The present disclosure provides methods and systems for providing a lateral center of gravity of an aircraft on an aircraft display. A fuel distribution in the aircraft fuel tanks is determined. A lateral center of gravity of the aircraft is determined based on the fuel distribution. The lateral center of gravity is sent to the aircraft display. The present disclosure further provides an aircraft display for displaying the lateral center of gravity of an aircraft.