Abstract: The motor vehicle (1) comprises at least one rear driving wheel (5) and two front steered wheels (7?, 7?). A tilting four bar linkage (11) allows the motor vehicle to perform a tilting movement, for example, when cornering. Support arms (21?, 21?) for front steered wheels (7?, 7?), which rotate around steering axes (21A?, 21A?) and are joined to each other by a steering bar (23), are associated with the tilting four bar linkage. Each wheel is constrained to the respective support arm with the interposition of a suspension (33; 33?). A tilting locking device comprises a brake (53?, 53?) which locks the springing movement of the respective suspension and the tilting movement of the four bar linkage.

Abstract: A straddle type electric vehicle comprises a main frame, a motor unit including an electric motor, a battery that supplies power to the motor unit, and a control unit that executes drive control of the motor unit. The main frame includes a left and right pair of portions, and at least a portion of the motor unit is disposed at a position overlapping the main frame in a side view of the vehicle.

Abstract: A drop-out mounting structure of a bicycle frame to inhibit a drop-out member from being separated from the bicycle frame is disclosed. The drop-out mounting structure of the bicycle frame for mounting a drop-out member as a wheel mounting unit to a drop-out mounting unit of a bicycle frame through a bolt may include an assembly slot formed at the drop-out mounting unit to insert the drop-out member inside the drop-out mounting unit and a stopper unit formed at an upper end part of the drop-out member with a length that is longer than an opening end of the assembly slot.

Abstract: A system and method for utilizing an active valve customizable tune application is disclosed. The system includes a mobile device having a memory, an active valve tune application, and at least one processor. The processor initiates the active valve tune application, receives, from a database, an active valve suspension tune having a number of performance range adjustable settings, and receives user related input information. At least one of the performance range adjustable settings is modified based on the received input information to generate a modified active valve suspension tune. The system includes an active suspension of a vehicle, wherein the modified active valve suspension tune is implemented by the active suspension.

Abstract: Various embodiments of a pedal for use on a device such as a bicycle or stationary bicycle are provided. A pedal may include a pedal body member having an internal cavity. The pedal may include an axle having a shaft adapted to extend into the internal cavity. The pedal body member may be adapted for transverse or side-to-side rotatable movement relative to a longitudinal axis of the axle shaft. The pedal body member may be self-centering and include one or more springs (such as coil, leaf, cantilever, torsion, etc., for example) to apply force to move the pedal body member toward a home or resting position relative to the axle shaft. The pedal may be adapted so that the user's foot can be placed on either a top surface or a bottom surface of the pedal body member.

Abstract: A bicycle derailleur includes a base member mountable to a bicycle frame and a cage assembly moveably coupled to the base member. One or both of a motor and/or electrical generator system may be coupled to and moveable with the cage assembly. The motor is operable to move the cage assembly. The electrical generator system includes a generator and a generator drive system.

Abstract: A rear gearshift mechanism for installation on a bicycle frame coaxial with a rear-wheel axis has a base element, a pivot mechanism, a movable element and a chain guide. The base element includes an attachment end for installation on the bicycle frame. A first arm and a second arm of the attachment end are arranged spaced apart from one another in an axial direction and, by an associated adapter which has a thread, are configured for the installation of the gearshift mechanism on an associated bracket portion, in particular a dropout or frame hanger. The first arm is arranged on an inner side of the bracket portion, and the second arm is arranged on an outer side of the bracket portion. The base element is designed with a setting device by which the base element can be pivoted in a chain tensioning direction.

Abstract: A harmonic drive system for a pedal-electric-cycle comprises a transmission gear device including a wave generator assembled by an elliptical cam and a flexible bearing, a flexible-flexspline, a rigid-circular-spline having rigid-circular-spline internal gear teeth, a gear set, and a one-way clutch having an inner surface defining a space for containing a spindle of the pedal-electric-cycle. A first end of the flexible-flexspline has flexible-flexspline external gear teeth for meshing with the rigid-circular-spline internal gear teeth and an inner surface defining a space for containing the wave generator. The gear set has a first input portion connected to a second end of the flexible-flexspline, a second input portion having an inner surface defining a space for containing the one-way clutch, and an output portion connected to a sprocket of the pedal-electric-cycle. The first input portion has a first-input rotational axis. The second input portion has a second-input rotational axis.

Abstract: A multiline ring anchor and a method for installing the multiline ring anchor is disclosed herein. The multiline ring anchor can be used for mooring systems for including, but limited to, arrays of offshore floating offshore wind turbines, wave power, and floating barriers.

Abstract: A portable marine anchoring device maximizes holding capacity while anchored into the ground. The device is fabricated from lightweight aluminum.

Abstract: A novel rotatable hull that generally includes a hull that is capable of rotating around an attachment point where it is connected to a vessel. In preferred embodiments, an outdoor motor mounted to the rotatable hull will turn to vector thrust and apply a moment to rotate the hull around a nominally vertical axis where the hull connects to the vessel. The invention also is directed to a vessel, which employs a plurality of rotatable hulls. A plurality of rotatable hulls can be arranged into a tripod, square or other stable geometric configuration and connected by a structure to form a vessel that can move in any direction along the plane of the surface of the water with or without changing the yaw axis orientation of the connecting structure. This may be useful in applications such as catching objects that are descending from the sky.

Abstract: The invention is directed to a propeller hubcap and method for installing a propeller hubcap which includes attaching a propeller hubcap to main propeller where the main propeller has at least two blades and a shaft and where the shaft has a diameter of from 2.5 inches to 6 inches. The propeller hubcap includes a central body and propeller blades, where the propeller blades are timed with the blades of the main propeller. A thick and thin nut are provided on the main propeller shaft where the thick or thin nut which is positioned further from the main propeller is tapped by multiple holes which have received a fastener. The fasteners attach the propeller hubcap to the main propeller shaft via complementary holes in the central body of the propeller hubcap.

Abstract: A method is for making a marine drive for propelling a marine vessel in water. The method includes providing a gearcase; installing a propeller shaft assembly that extends forwardly from the gearcase; coupling front and rear propellers to the propeller shaft assembly, forwardly of the gearcase, such that rotation of the propeller shaft assembly causes rotation of the front and rear propellers, respectively, which thereby propels the marine vessel in the water; and reducing deleterious effects of cavitation on the gearcase by the combination of forming the gearcase with a wide trailing end portion, in particular to maintain pressure alongside the gearcase, and configuring the front and rear propellers so that the front propeller absorbs more torque/thrust load than the rear propeller during said rotation.

Abstract: An aircraft fuselage includes an element forming a skin and a load-carrying structure supporting the element forming the skin. The load-carrying structure includes a plurality of elements forming a spar disposed parallel to an axial direction defined by the fuselage and a plurality of elements forming a frame disposed spaced apart along the axial direction. Each element forming a frame being arranged substantially perpendicularly to the elements forming a spar, where the element forming the skin is fastened on an external perimeter of each element forming a frame by means of fastening elements configured to keep the element forming the skin away from the external perimeter and where the element forming the skin is made of a transparent material.

Abstract: A latch (12) intended for assembling a removable panel (18) to a structure (14), notably that of an aircraft, includes a bracket (30) fixed to the panel; a keeper (32) and a push button (34) hinged to the bracket; a torsion spring (40) comprising two arms respectively in abutment on the keeper and the push button. The latch is movable between a closed configuration, in which the keeper is in contact with the push button, and an open configuration, in which the keeper is spaced apart from the push button. The latch further includes a roller (42) rotatably supported on an arm (86) of the spring; and the keeper includes a profile (58) on which the roller moves when the latch is moved between the closed and open configurations.

Abstract: An aircraft comprising a wing having a spanwise lift distribution extending from a root to a tip, the lift distribution defining an inboard region defining a positive lift contribution, an outboard region defining a negative lift contribution, and an intermediate region defining a neutral lift contribution, the neutral region being spaced from the tip and from the root. A propulsion system is provided, comprising a wing mounted propulsor. The wing mounted propulsor has a rotational axis (x) positioned substantially at a span of the wing where a value of ?Lift/?Span is at a maximum for the span of the wing, and may be located at the intermediate region along the span of the wing.

Abstract: An aircraft wing is provided having a wing leading edge, a cut-out opening in the wing leading edge, a telescopic tube extending through the cut-out opening and connected to an internal duct of a wing leading edge slat to establish fluid communication with heated air associated with an aircraft anti-icing system, wherein the telescopic tube is moveable between retracted and extended conditions in response to the wing leading edge slat being moved between slat retraction and deployment positions, respectively, and a cover assembly comprising a cover member operatively connected to the telescopic tube to close the cut-out opening and allow synchronous movement of the cover member with the telescopic tube in response to the telescopic tube being moved between the retracted and extended conditions thereof.

Abstract: A wing for an aircraft, including a main wing, a slat, and a connection assembly movably connecting the slat to the main wing, such that the slat is movable between a retracted position and at least one extended position. The connection assembly includes a first connection station and a second connection station spaced apart from the first connection station in a wing span direction. The object, to prevent the slat from skewing, is achieved in that the connection assembly includes a sync shaft coupling the first connection station to the second connection station for sync movement of the first and second connection stations.

Abstract: A hinge-line actuator has: a drive shaft; first and second ground gears spaced apart along the drive shaft, wherein the first and second output gears include first and second contoured outer gear surfaces; and an output gear disposed on the drive shaft and disposed between the first and second ground gears, wherein the output gear includes a third contoured outer gear surface; an actuator housing that includes: contoured first, second and third gear seats that, respectively, seat the first, second and third outer gear surfaces.

Abstract: In an aspect a system for fly-by-wire flight control configured for use in electric aircraft including at least a sensor, wherein the sensor is communicatively connected a pilot control and configured to detect a pilot input from the pilot control and generate, as a function of the pilot input, command datum. A system includes a flight controller, the flight controller including a computing device and configured to perform a voting algorithm, wherein performing the voting algorithm includes determining that the sensor is an allowed sensor, wherein determining that the sensor is an allowed sensor includes determining that the command datum is an active datum, determining the command datum is an admissible datum, generating, as a function of the command datum and the allowed sensor, a control surface datum wherein the control surface datum is correlated to the pilot input.

Abstract: Aspects relate to systems and methods for controlling landing gear of an aircraft. An exemplary system includes a nose gear located at a nose of the aircraft, where the nose gear includes a nose piston configured to allow for displacement of a nose wheel relative the aircraft, a main gear located aft of the nose gear, where the main gear includes a main piston configured to allow for displacement of a main wheel relative the aircraft, a hydraulic circuit in fluidic communication with each of the nose piston and the main piston, and a compliant element in fluidic communication with the hydraulic circuit and configured to provide a compliant response at one or both of the nose piston and the main piston.

Abstract: A wheel assembly includes an inboard wheel portion having a rim and a disk. A radially inward surface of the rim and an inboard surface of the disk define a wheel well cavity configured to house a brake assembly. The wheel assembly also includes a torque bar (e.g., a torque bar of the brake assembly) mounted to the inboard wheel portion. Further, the wheel assembly includes a retainer coupled to the torque bar and disposed radially between the torque bar and the radially inward surface of the rim of the inboard wheel portion. The retainer includes a first end, a second end opposite the first end, and a body extending between the first end and the second end. The body includes opposing longitudinal sides configured to respectively engage and retain a respective heat shield segment of a segmented annular heat shield.

Abstract: A method of reducing the noise generated in-flight by a vortex wake caused by each first blade of a main rotor of a hybrid helicopter. The hybrid helicopter includes a main rotor, at least two wings and at least one propeller. The method enables a stabilized flight phase on the level or with a non-zero aerodynamic slope to be implemented by determining a first value of the pitch of the second blades of each propeller and an angle of incidence of the main rotor as function of the flight conditions, then by applying the first pitch value to each propeller and by applying the angle of incidence to the main rotor so as to direct the vortex wake to limit the noisy interactions between the vortex wake and the other first blades and/or the second blades.

Abstract: A compound rotorcraft comprises a fuselage, a rotor coupled to the fuselage and a wing mounted to the fuselage. The rotorcraft further comprising a first outboard propeller, a first inboard propeller, a second outboard propeller, and a second inboard propeller. The first outboard propeller having a propeller body and propeller blades, the body mounted to a first wing-half at a first incidence angle. The first inboard propeller having a propeller body and propeller blades, the body mounted to the first wing-half between the first outboard propeller and the fuselage at a second incidence angle. The second outboard propeller having a propeller body and propeller blades, the body mounted to a second wing-half at a third incidence angle. The second inboard propeller comprising a propeller body and propeller blades, the body mounted to a second wing-half between the second outboard propeller in the fuselage at a fourth incidence angle.

Abstract: A vertical-takeoff-and-landing (“VTOL”) aircraft including a non-VTOL aircraft equipped for forward takeoff and flight and a modular boom system interoperably coupled to the non-VTOL aircraft. The modular boom system includes a first modular boom and a second modular boom. The first modular boom includes a first rocket-turbine engine. The first modular boom is mounted to a first wing of the non-VTOL aircraft. The second modular boom includes a second rocket-turbine engine. The second modular boom is mounted to a second wing of the non-VTOL aircraft.

Abstract: An aeronautical car includes a ground-travel system including a drivetrain; an air-travel system including a detachable portion configured to house a propulsion device configured to provide thrust and to be driven by the drivetrain when the detachable portion is connected to the aeronautical car, and at least one flight mechanism configured to provide lift once the aeronautical car is in motion; and a weather manipulation device. The weather manipulation device may be configured to manipulate at least one aspect of a weather condition while the aeronautical car is in the air.

Abstract: The present disclosure generally relates to reusable containers having a locking feature and geographic location tracking capabilities. In particular, the present disclosure relates reusable containers having a locking feature and geographic location tracking capabilities for autonomous delivery of goods.

Abstract: A system for anchoring unmanned aerial vehicles to surfaces includes a landing pad configured to be installed on an agricultural machine, with the landing pad defining a landing surface. Furthermore, the system includes an unmanned aerial vehicle (UAV) configured to land on the landing surface and a top surface of a field across which the agricultural machine is traveling. The UAV, in turn, includes an anchoring device configured to engage soil within the field to anchor the UAV to the field when the UAV has landed on the top surface of the field. Additionally, the anchoring device is further configured to engage the landing pad to anchor the UAV to the landing surface when the UAV has landed on the landing pad.

Abstract: A constant tension tether management system for tethered aircraft includes a ground station for operatively coupling to an unmanned aerial vehicle. The ground station includes a spool rotatably disposed within the ground station and adapted to support a tether thereon. A first pulley is rotatably mounted within the ground station along a tether travel path. A second pulley is rotatably disposed within the ground station and moves in translation along the tether travel path. The first pulley is disposed along the tether travel path between the spool and the second pulley.

Abstract: A rotorcraft includes a body and a plurality of rotary-wing parts. The body has a front-end portion, a rear-end portion, two side portions, and a reference plane passing through the front-end portion, the rear-end portion, and the two side portions. The plurality of rotary-wing parts are disposed to the body. Each of the rotary-wing parts includes at least one blade and a shaft coupled to the at least one blade. The at least one blade is rotated around an axis of the shaft. An angle between the axis of the shaft and a normal line of the reference plane is between 5 and 30 degrees. The rotorcraft can provide additional lift force, to help reduce the weight of the rotorcraft.

Abstract: A takeoff and landing device, includes: a fixing devices or a communication unit configured to be able to switch between a first state that is a state of preventing the unmanned aerial vehicle from taking off from the takeoff and landing device and a second state that is a state of not preventing taking off; a weight acquisition unit configured to acquire weight of the article that the unmanned aerial vehicle delivers; and a takeoff controller or a takeoff controller configured to switch a state of the fixing devices or the communication unit to the first state or the second state on the basis of the weight of the article acquired by the weight acquisition unit and of a reference value for determining whether it is an overload.

Abstract: Techniques are provided for implementing automated contagion detection and remediation (ACDR) features to detect and remediate environmental contagion conditions. For example, ACDR techniques can be used to target contagion contamination on surfaces in a trafficked area, rather than focusing detecting and remediating human symptoms. ACDR systems can include swarms of specially configured drones under control of one or more centralized controllers to detect presence of one or more types of pathogens on surfaces and to classify detected contagion events. In some embodiments, upon such detection, the same or other specially configured drones can be triggered to remediate the detected condition by removing the pathogen by disinfecting surfaces, by cordoning off infected areas, and/or in other ways. Some embodiments can further log and aggregate data relating to detected contagion events to support tracking, remediation, enforcement, protocol updating, research, and/or other efforts.

Abstract: Described herein are methods and systems for picking up, transporting, and lowering a payload coupled to a tether of a winch system arranged on an unmanned aerial vehicle (UAV). For example, the winch system may include a motor for winding and unwinding the tether from a spool, and the UAV's control system may operate the motor to lower the tether toward the ground so a payload may be attached to the tether. The control system may monitor an electric current supplied to the motor to determine whether the payload has been attached to the tether. In another example, when lowering a payload, the control system may monitor the motor current to determine that the payload has reached the ground and responsively operate the motor to detach the payload from the tether. The control system may then monitor the motor current to determine whether the payload has detached from the tether.

Abstract: The present disclosure provides a swivel stop comprising a rotating member, a first boss coupled to the rotating member and a second boss coupled to the rotating member, and a second plate having a first interference surface and a second interference surface. An interference between the first boss and the first interference surface and the second boss and the second interference surface tends to limit the rotation of the rotating member with respect to the second plate. The swivel stop may further comprise a rail wherein the second plate is configured to translate along the rail.

Abstract: Disclosed is a modular seat for aircraft. The system has a frame that is able to be interconnected with other frames laterally. Since each lateral frame has the same pivot points (when viewed from the side), the linked seats rotate together. The seats also include buckle lugs which enable a particular seat to be used on either side of the aircraft.

Abstract: An adjustable armrest assembly provides for quick and easy height and tilt adjustments to the armrest. Generally, the armrest assembly disclosed herein includes a base, an armrest, and one or more shafts extending from the base and being pivotably coupled to the armrest. By moving the one or more shafts relative to the base, the height and/or tilt of the armrest relative to the base can be adjusted.

Abstract: An aircraft air conditioning pack assembly including an air conditioning pack configured to discharge heat, and an exterior panel positioned in close proximity to the air conditioning pack. The exterior panel includes an opening defined therein, a first side facing towards the air conditioning pack, and a second side defining an exterior surface configured to be in communication with a free stream airflow. At least a portion of the air conditioning pack is disposed within the opening to facilitate transferring heat from the air conditioning pack to the free stream airflow.

Abstract: An article of manufacture may include a tangible, non-transitory computer-readable storage medium having instructions stored thereon for controlling deployment of aircraft escape and ejection seat subsystems. The instructions, in response to execution by a first sequencer, cause the first sequencer to perform operations which may comprise receiving a power input, determining a seat location and a seat identity of a first ejection seat in which the first sequencer is installed, determining an ejection mode, sending a first deploy command to an escape path clearance subsystem, determining a deployment sequence for a seat rocket catapult subsystem and a plurality of ejection seat subsystems of the first ejection seat based on the seat location, the seat identity, and the ejection mode, sending a second deploy command to the seat rocket catapult subsystem, and sending a series of third deploy commands to the plurality of ejection seat subsystems.

Abstract: An assembly including a connecting device, connecting first and second parts, including first and second links positioned on respective opposite sides of the first and second parts and an interleaved stiffener, positioned between the first and second links, having a first contact face oriented toward the first link and a second contact face oriented toward the second link, parallel to the first face, the first and second contact faces being separated by a distance equal to that separating the first and second links. This interleaved stiffener makes it possible to limit the risks of bending of the links when they are loaded in compression.

Abstract: A hybrid electric engine control module (ECU) configured to be operatively connected to a hybrid electric aircraft powerplant having a heat engine system and an electric motor system to control a torque output from each of the heat engine system and the electric motor system, the ECU being configured to determine whether the electric motor system and/or the heat engine system are in a normal mode such that the electric motor system and/or the heat engine can provide a predetermined amount of torque (e.g., full power). The ECU can be configured to receive a total torque setting and split output power between the electric motor system and the heat engine system in accordance with the normal mode as a function of the total torque setting. The ECU can be configured to detect and command recharging or regenerating of the battery system in some flight conditions.

Abstract: An acoustic panel including a first face sheet having a plurality of openings; a core attached to the face sheet, the core comprising a plurality of cells each having cell walls; and a plurality of noise attenuating features each comprising at least one of the openings in combination with one of the cells, wherein the openings are disposed away from the cell walls so that the noise attenuating features suppress the transmission of acoustic waves in acoustic communication with the openings.

Abstract: An arrangement for cooling at least one power module of a power converter is disclosed herein. The arrangement includes power semiconductor components. The power module is arranged in a drive flow of an engine in such a way that the drive flow flows around cooling ribs of the power module. The disclosure also relates to a power converter, (e.g., an inverter), including an arrangement of this kind and an aircraft, (e.g., an airplane), including a power converter of this kind.

Abstract: A system and method for inerting a fuel tank is disclosed. A fluid including non-condensable gas is directed from a vapor space in the fuel tank to a suction port of an ejector, and a motive fluid is directed to a motive fluid port of the ejector. The motive fluid and the non-condensable gas fluid are combined in the ejector and are directed from an outlet port of the ejector to the fuel tank. An inert gas is provided to the ejector motive fluid port, or to the second flow path, or to the first flow path.

Abstract: A support assembly may include a support structure and a P-clamp attached to the support structure. The P-clamp may include a clamp body defining an opening, a mounting base structured and arranged to engage the support structure, and a connecting section interconnecting the clamp body and the mounting base. The P-clamp may be arranged in an inverted upright position where the mounting base is attached to the support structure underneath the clamp body relative to a direction of gravity. The P-clamp may yield at the connecting section upon an application of a load for to the clamp body that is equal to or greater than a predetermined applied load three threshold. The support assembly may be useful in an aircraft fuel line installation for supporting a fuel line from the support structure.

Abstract: Disclosed is a direct current power supply. The direct current power supply includes a voltage output defining a voltage rail and a ground. The direct current power supply includes a holdup capacitor operable to conduct with the voltage output. The direct current power supply includes a redundant power supply connected in series with the holdup capacitor between the voltage rail and the ground of the voltage output to provide the voltage output. The direct current power supply includes a first switch disposed between the holdup capacitor and the redundant power supply operable to create a conductive path between the holdup capacitor and the redundant power supply.

Abstract: A monitoring system and method are provided for real time monitoring of flaps, landing gears, or tail skids to determine safe taxi, takeoff, and flight readiness. Monitoring units, including scanning LiDAR devices combined with cameras or sensors, mounted in aircraft exterior locations produce a stream of meshed data that is securely transmitted to a processing system to generate a real time visual display of the flaps, landing gears, or tail skid for communication to aircraft pilots to ensure safe aircraft taxi, takeoff, and flight readiness. Actual flap position alignment with optimal flap setting, proper retraction and extension positions of landing gears, and tail skid condition is ensured. Safety of aircraft taxi, takeoff and flight and airport operations are improved when the present system and method are used to prevent incidents related to misaligned flaps and improperly positioned landing gears or tail skids.

Abstract: Disclosed are unmanned aerial vehicle (UAV) positioning mechanisms for moving a UAV across a surface. The positioning mechanisms comprise a first guide assembly arranged opposite to a second guide assembly. A drive system is arranged to move the first guide assembly towards the second guide assembly and guide the UAV from a first position to a second position.

Abstract: A method for forming an aircraft component includes forming an inner portion of the aircraft component. The method further includes forming an outer layer of the aircraft component using extrusion of an elastomeric material. The method further includes coupling the outer layer of the aircraft component to the inner portion of the aircraft component.

Abstract: Tooling for placing a propulsive assembly from a horizontal position to a vertical position includes a front tool and a rear tool. The front tool has a first assembly with a frame configured to be positioned and maintained with respect to a front casing. The frame has a first connection interface configured to be connected to a first lifting system such that the frame is movable about an axis of rotation (R). The front tool also has a second assembly with a shaft configured to be positioned and maintained with respect to a rotor and a member for connection between the first assembly and the second assembly. The tooling further includes a rear tool configured to be positioned and maintained with respect to the rear casing. The rear tool has a second connection interface configured to be connected to a second lifting system.

Abstract: A movable carriage system for an aircraft element, such as an aeroplane engine, has a first movable module (10) and a second movable module (20). Each movable module has a frame (12, 22) equipped with at least three wheels, a lifting device adapted to be able to move said aircraft element at least in a vertical direction, and at least one link arm (16, 17) adapted to be able to secure together the frame of said first module and the frame of said second module and to allow data to be transferred between them. The movable modules are adapted to be able to be controlled in a mutually coordinated manner.