Abstract: A vehicle, vehicle frame, and steering system usable with the vehicle and vehicle frame. The steering system including a first and second knuckle mounted to a vehicle frame and configured to rotate with respect to the vehicle frame to turn the wheels, and a pitman arm link rotatable relative to the vehicle frame. The steering system further includes a first tie rod operably connected to the first knuckle to the pitman arm link bracket via a pitman arm and pitman connector, and a second tie rod connecting the second knuckle to the pitman arm link. A pitman connector is rotatably operatively connected to the pitman arm link, wherein the pitman arm thereby transfers pivoting or rotational motion applied via a steering input from the pitman arm to the pitman arm link, to respective knuckles via the first and second tie rods.

Abstract: The invention relates to a transport cycle (2) comprising a frame and at least three wheels (4) of which at least two wheels (4) are designed as side wheels (6) spaced at a certain distance from one another in a direction extending transversely to a direction of travel of the transport cycle (2), wherein said transport cycle (2) has a storage area. The transport cycle (2) has two lateral supports (5) which are spaced at a certain distance from one another transversely to the direction of travel, laterally delimit, as the storage area, a storage space (10) having an access opening (11), and form therebetween the storage space (10) having an access opening (11) for inserting a transport box. The invention also relates to a transport system comprising the transport cycle and a transport box which can be inserted into the storage space.

Abstract: A sit-astride amphibious vehicle configuration which supports a high performance envelope both on land as well as in water. The vehicle has a planing hull and four retractable wheels. Handlebars provide for directional control in both modes of operation. Each road wheel is retractable by pivoting through at least 45° so as to maximize ground clearance when in the land mode of operation and to minimize drag at substantial lean angles when in the marine mode of operation. While a jet drive may remain directly connected to the engine at all times, the driven wheels are only connected during land mode via a speed-change transmission. The entire power train is supported by a frame that is separable from the hull which in turn has a detachable top deck portion, whereby such configuration simplifies the construction, repair and servicing of the vehicle.

Abstract: An electric transformable scooter that can transform between a stand-on configuration and a ride-on configuration. The scooter has a fixed frame member at the front to which the front wheel and handlebar are mounted, and movable frame member that extends between the rear wheel and the fixed frame member. The front end of the movable frame member slides or otherwise adjusts to either a lower position or an upper position on the fixed frame member. When the movable frame member is at the lower position and locked thereat, it is generally horizontal, and its top surface defines a stand-on floorboard for stand-on operation. When the movable frame member is slid to its upper position and locked thereat, it is inclined from front to rear, and portion rotates away and locks thereat to become a seat for ride-on operation.

Abstract: A foldable vehicle comprising a vehicle frame main body. The vehicle frame main body comprises a crossing member that goes through the front end and the back end of the vehicle. The crossing member is provided with a folding mechanism (3) that reduces the length of the foldable vehicle. During the folding process, only the length of the foldable vehicle is reduced, and the height of the foldable vehicle is unchanged, thereby addressing the problem in the prior art that the height of a foldable vehicle substantially increases after folding, thus enabling the folded vehicle to be placed within a regular accommodation space more conveniently, and effectively enhancing the portability of a foldable vehicle.

Abstract: A folding vehicle has a frame body which has a front split ring (1) and a rear split ring (2) connected by a folding mechanism (3), and the front split ring (1) and the rear split ring (2) form a closed loop body after folding, thereby reducing the space occupied by the folding vehicle, and at the same time reducing the material consumption, significantly reducing the vehicle weight, and improving the portability.

Abstract: A clamping mechanism is provided, the clamping mechanism have two clamps, a tensioning conduit corresponding to each of the clamps, and an actuator for simultaneously tensioning the two clamps by way of the tensioning conduits. Each clamp has a bracing element and a gripping segment, and when the clamps are tensioned along the tensioning conduit, the gripping segment of each clamp is drawn towards the corresponding bracing element. Also provided is a bicycle drive assembly, the assembly has two clamps for fixing to a bicycle, a drive mechanism for driving a bicycle wheel, and two elongate supports extending from the drive mechanism to corresponding clamps. When applied to a bicycle, a wheel of the bicycle passes partially between the elongate supports.

Abstract: A vehicle includes a propulsion power source, a handlebar, an output adjusting grip, and a torque operation member. The handlebar is operable to steer the vehicle. The output adjusting grip is disposed on either a right or left portion of the handlebar operably so that an output level of the propulsion power source is adjusted by rotating the output adjusting grip relative to the handlebar. The torque operation member is operable to issue a command to change a torque output characteristic of the propulsion power source. The torque operation member is disposed on the same right or left portion of the handlebar with the output adjusting grip rotatably integrally with the output adjusting grip.

Abstract: To provide a rear wheel braking device for a motorcycle that can reduce an unsprung mass and the number of pieces of components on the rear wheel side of a shaft drive type motorcycle. In a rear wheel braking device for a motorcycle transmitting a drive force of a power unit of a motorcycle to a rear wheel through a drive shaft that extends in a vehicle longitudinal direction, the drive shaft includes a propeller shaft that is connected to a rear end of an output shaft through a universal joint, the output shaft protruding to the vehicle body rear side from a case member of the power unit. A brake disk is attached to the output shaft, the brake disk being braked by a rear wheel brake caliper. The rear wheel brake caliper is fixed to a bracket that is arranged in the case member, and is disposed on the vehicle body upper side of the brake disk.

Abstract: A method for automatic retraction of a pedal of a bicycle. A first electric actuator is provided on a crank, and the pedal is driven to be retracted by the first electric actuator to complete a first retraction, so that long side of the pedal is changed into a front-rear direction from a left-right direction; a second electric actuator mounted on a bicycle frame drives the crank to idle, and the pedal is gradually straightened in the first retraction process to be parallel with the plane of the bicycle frame to complete a second retraction of the pedal. Using this method, the pedal can be conveniently retracted, and the transverse (left-right) occupying space is minimized, thereby facilitating the automatic storage and saving the storage space.

Abstract: A universal, quick release foil mounting system is disclosed. The device is comprised of three mam parts: a first part being a ‘mount plate’ that is fixedly connected to existing kite surfing, windsurfing and standup paddle boarding foils by means of fasteners; a second part being a ‘base plate’ that is fixedly secured to the mast track of existing kite surfing, standup paddle hoarding (SUP) and windsurfing boards—also affixed by means of fasteners; a third part being a quick disconnect system on said mount plate or base plate comprised of, but not limited to catch tabs, locking pins and slide locks etc. The mount plate is configured to receive the base plate and temporarily join the foil mast to the board. An object of the invention is to allow any foil having standard 165 mm×90 mm (6.5?×3.5?) hole mounts (as well as other dimensions) to be quickly installed or removed from a board.

Abstract: A closing device configured to close an outer shell opening of a surface ship, including several substantially vertically mounted shutter lamellas and a drive device by means of which the shutter lamellas can be actuated such that they move between a closed position and an open position.

Abstract: This invention relates to a multi-purpose, eco-safe bag for your gear which can be used interchangeably as a sand anchor to keep your stand up paddle board, kayak, or raft anchored in position while you are snorkeling, fishing, doing yoga, or just relaxing and hanging out in the water. Fill The SUPSAC with beach sand and attach to a leash or any length of rope to secure. The SUPSAC may also be used to secure beach umbrellas or canopies. This product is easily transportable at approximately 14 inches by 11 inches, light weight and multi-purpose. This product has no sharp blade type pieces which could harm the ocean environment, sea life, or another person. This product will not get hooked onto seagrass, corals or stuck on rocks as a claw type anchor would therefore making it an eco-safe product. When finished, simply empty the sand back into the water, returning it to its natural environment, re-pack your gear inside the canvas bag and continue on your paddle adventures.

Abstract: A semisubmersible floating platform (1) for supporting at least one wind turbine, comprising four buoyant columns (3), each of them being attached to a ring pontoon (2); a transition piece (4) configured to support one wind turbine, disposed on the buoyant columns (3); and a heave plate (5) assembled to the internal perimeter of the ring pontoon (2). The ring pontoon (2) comprises four pontoon portions forming a quadrilateral-shaped ring pontoon (2) wherein the first end of each column (3) is attached to a respective corner of said quadrilateral-shaped ring pontoon (2). The heave plate (5) is located in the internal perimeter of the ring pontoon (2), both defining a hollow. The pontoon (2) is preferably divided into a plurality of compartments or construction blocks that may be filled with fixed ballast, such as concrete.

Abstract: The present disclosure relates to a houseboat assembly formed from a cabin assembly secured to a hull assembly. In some version of the houseboat assembly, the hull assembly may include a runoff flange. The runoff flange may include an inner flange, an outer flange, and a riser extending between the inner flange and the outer flange. The outer flange may extend along an imaginary longitudinal outer flange axis and the riser may extend along an imaginary longitudinal riser axis whereby the riser axis intersects the outer flange axis at an angle. In some versions of the houseboat assembly, the angle is an acute angle. More specifically, the angle may be between thirty and sixty degrees. In some versions of the houseboat assembly, the cabin assembly is secured to the inner flange of the runoff flange. Cross-members and deck boards may be secured to a roof of the cabin assembly.

Abstract: A personal water craft includes a hull; a deck attached to, or integral with, the hull; a foot well having a foot well floor that is configured to receive a foot of a user of the personal water craft; and a drainage system configured to drain liquid from the foot well, the drainage system having a tube extending from the foot well floor to a location outside the hull.

Abstract: A rescue assist device for use with a throwable personal floatation device is provided. The device includes a top handle member, a bottom member including a first coupling feature, and a first side member including a first end and a second end, wherein the first end is connected with the top handle member, and wherein the second end is connected with the bottom member. The device also includes a second side member including a first end and a second end, wherein the first end is connected with the top handle member, and wherein the second end is connected with the bottom member. Further, a first end of a retaining arm is pivotably connected with the first side member, and a second end of the retaining arm includes a second coupling feature that is configured for being releasably engaged with the first coupling feature.

Abstract: A ventilator 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 tubular ventilating sleeve which provides separate passageways for supplying fresh air and exhausting exhaled air through the faceplate. The tubular ventilating sleeve has a tubular body and an inhalation conduit defining a passageway that connects a snorkel coupling and to an inhalation tube of a ventilating device. The tubular inhalation conduit fluidly connects a snorkel coupling passageway of said scuba-enabled mask to said inhalation tube of said ventilating device.

Abstract: A bionic underwater robot for achieving a variety of motions is disclosed. The bionic underwater robot includes a head and one or more tail structures. Each of the one or more tail structures includes one or more joint structures. Each of the one or more joint structures includes a connection plate, and a modular assembly, comprising an upper servo motor, a lower servo motor, and a bevel gear mechanism, is motorized for performing various movement motions of the joint structure. The bevel gear mechanism is integrally formed by an intermediate bevel gear, a first bevel gear, and a second bevel gear. The upper servo motor drives the first bevel gear from a first side of the modular assembly, while the lower servo motor drives the second bevel gear from a second side.

Abstract: The invention relates to the field of shipbuilding and more specifically to the screw propeller for a pod drive of a vessel, particularly an ice-going vessel, providing movement both ahead and astern in icy conditions where the ice is traversable, while also providing steering for the vessel, and to a pod drive comprising said screw propeller. To reduce the weight, and consequently the cost, of the pod drive, the screw propeller comprises a propeller hub, made so that it can be rigidly attached to the conical tailpiece of the propeller shaft, and screw propeller blades, each comprising a blade foil and a blade flange made in one piece, mounted on the propeller hub. The blade foil passes into the blade flange via a fillet joint forming the weakest portion for the possible destruction of the blade in the cross section of its foil, located immediately adjacent to the fillet joint.

Abstract: An outboard motor lifting device includes a hydraulic source, a first oil channel connecting the hydraulic source with a second chamber of a tilt cylinder, a second oil channel connecting the first oil channel with a second chamber of a trim cylinder, a third oil channel connecting the hydraulic source with a first chamber of the tilt cylinder, a check valve provided between the second chamber of the tilt cylinder and a connection position between the first and second oil channels, a fourth oil channel connected to the third oil channel, and a switch valve provided on the second oil channel and connected with the fourth oil channel. The switch valve has a connection state where communication between the first oil channel and the second chamber of the trim cylinder is closed, and communication between the fourth oil channel and the second chamber of the trim cylinder is open.

Abstract: A system for maneuvering a boat including a hull and an outboard motor includes a left tilt shaft, a right tilt shaft, a steering shaft support, and a hydraulic cylinder. At least a portion of the hydraulic cylinder is between the left tilt shaft and the right tilt shaft. The hydraulic cylinder exerts a steering force on the outboard motor to rotate the outboard motor about a steering shaft. A hydraulic pump supplies hydraulic fluid to the hydraulic cylinder. One of the left tilt shaft and the right tilt shaft includes a first hole. A portion of the stroke range of the hydraulic cylinder is located within the first hole.

Abstract: A clamp assembly for connecting a rudder to an aquatic device having a body with a first end, a second end, a top and a bottom. A clamp having a screw connected to a pivot pin disposed within a clamp head is removably connected to the top of the body for selectively applying a clamping force on the body. The clamp handle in some bodies tapering to an end to allow placement within a retaining slot of a fin box.

Abstract: Various embodiments for a foldable quad-rotor (FQR) inspired by an origami mechanism are disclosed herein. The FQR can fold its arms during flight to enable aggressive turning maneuvers and operations in cluttered environments. A dynamic model of folding is built for this system with the collected data, and a feedback controller is designed to control the position and orientation of the FQR. Lyapunov stability analysis is conducted to show that the system is stable during arm folding and extension, and motion planning of the FQR is achieved based on a modified minimum-snap trajectory generation method.

Abstract: A stiffened structural component for an aircraft includes a first material sheet with a first surface, and at least one elongate bulge that bulges out in a direction transverse to the first surface in order to stiffen the structural component, wherein each of the at least one bulge comprises two edges that extend along the first surface, wherein a continuous bulging surface extends between the edges, and wherein the bulges are formed integrally into the first material sheet through pressing.

Abstract: A system for controlling turbulence of fluid flowing past a window includes an imaging device compartment defining an interior and an exterior separated by a window, wherein the window encloses at least a portion of the interior, wherein the exterior includes at least one turbulator on a side upstream of the window positioned to induce turbulence over the entirety of a boundary layer of the fluid flowing past the window for even heat transfer between the fluid and the window.

Abstract: An aircraft cabin door system has a cabin door having an outer side and an inner side, a drive device coupled to the cabin door for moving the cabin door into an open position, a first actuation device, a second actuation device, and an emergency chute unit coupled to the cabin door and having an emergency chute and an actuation mechanism. The emergency chute unit can be moved into an active state, in which opening the cabin door leads to activation of the emergency chute, and an inactive state, in which opening the cabin door does not lead to activation of the emergency chute. The emergency chute unit is in the inactive state when the cabin door is opened after actuation of the first actuation device. The emergency chute unit is in the active state when the cabin door is opened after actuation of the second actuation device.

Abstract: A flooring system for enclosures or vehicles, such as an aircraft flooring architecture, includes a flooring panel with at least an upper layer, a core ply, and a bottom layer. The bottom layer of the flooring panel has a top face and a bottom face, an upper layer of the flooring panel has an upper face and a lower face, and a core ply of the flooring panel has an upper surface bonded to the lower face of the upper layer and a bottom surface bonded to the top face of the bottom layer. The bottom face of the bottom layer is located on a structural floor of an enclosure or vehicle, such as the aircraft, and the bottom layer of the flooring panel slides over the structural floor.

Abstract: An aircraft wing is provided with a shutter mechanism to close a cut-out opening in the leading edge of the wing when a leading edge wing slat associated with the wing leading edge is moved to a deployed condition.

Abstract: Foldable raked wing tips having aerodynamic devices are disclosed. A disclosed example wing for use with an aircraft includes a fixed portion, and a folding portion proximate a distal end of the wing. The folding portion includes a raked surface. The wing also includes at least one of a feather or a winglet, and a hinge operatively coupled between the fixed and folding portions to enable the folding portion to fold relative to the fixed portion.

Abstract: An aircraft wing having a fixed wing and a wing tip device at the tip of the fixed wing is disclosed. The wing tip device being movable relative to the fixed wing between flight and ground configurations, the aircraft wing having a locking mechanism including a locking bore and a locking pin, the locking mechanism being configurable between a locked configuration, in which the locking pin is received in the locking bore, to lock the wing tip device in one of the flight or ground configurations, and an unlocked configuration in which the locking pin is withdrawn from the locking bore such that the wing tip device is moveable relative to the fixed wing, and wherein the locking pin is configured such that it has a replaceable tip.

Abstract: A system comprising an aerial vehicle or an unmanned aerial vehicle (UAV) configured to control pitch, roll, and/or yaw via airfoils having resiliently mounted trailing edges opposed by fuselage-house deflecting actuator horns. Embodiments include one or more rudder elements which may be rotatably attached and actuated by an effector member disposed within the fuselage housing and extendible in part to engage the one or more rudder elements.

Abstract: Link bar assemblies are provided to connect adjacent structural components (e.g., components of an aircraft such as connecting an underwing engine to the wing structure) having respective connection lugs. The link bar assemblies will include a link bar having opposed terminal ends which include circular bearings, bushings operatively received by the circular bearings of the link bar, and a bolt and pin assembly inserted through the bushings to connect the terminal ends of the link bar to the respective connection lugs of the adjacent structural components. At least one of the bushings includes a multi-faceted flange and defines an eccentric aperture (e.g., an elliptical aperture having major and minor axes) such that rotation of the bushing allows the eccentric aperture to become aligned with the mounting opening of a respective connection lug.

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: Closure devices and methods are provided for closing a stringer penetration space defined between a stringer and a wing rib of an aircraft wing section. According to certain embodiments, the closure devices will integrally include a forward face plate positioned in covering relationship to at least a portion of the stringer penetration space, and a rearwardly projecting attachment arm rigidly adapted for rigid attachment to the stringer so as to positionally fix the forward face plate relative to the stringer penetration space.

Abstract: A lift nacelle may comprise an airflow generator; a sidewall system coupled to the airflow generator and spanning in a first direction, wherein the sidewall system defines a nacelle interior space, wherein the airflow generator defines one of a forward boundary or an aft boundary of the nacelle interior space; and a lift body disposed in the nacelle interior space and spanning substantially perpendicular to the first direction and substantially perpendicular to an upward lift direction. The airflow generator may be configured to accelerate airflow in an aft direction into the nacelle interior space through the forward boundary of the nacelle interior space. The airflow may contact and/or interact with the lift body creating lift in response.

Abstract: A slat track roller assembly is provided so as to mount a slat track operatively associated with a wing leading edge slat for movements between retracted and deployed conditions relative to a leading edge of an aircraft wing. The slat track roller assembly may include at least forward and aft pairs of roller mechanisms connected to a respective one of opposed wing ribs of the wing leading edge in operatively rolling contact with a respective opposed lateral edge of the slat track. At least one of the roller mechanisms is positionally adjustable relative to the respectively opposed lateral edge of the slat track so as to compensate for mechanical tolerances that may be present.

Abstract: A wing for an aircraft including a main wing, slat, and connection assembly movable connecting the slat to the main wing and including an elongate slat track. A front end of the slat track is mounted to the slat and a rear end and an intermediate portion of the slat track are mounted to the main wing by a roller bearing that includes a guide rail mounted to the main wing and a first roller unit mounted to the rear end of the slat track and engaging the guide rail. The wing has redundant main load paths as the guide rail includes a guide rail primary structure engaging with the first roller unit, and an additional reinforcement structure additionally reinforcing the guide rail primary structure in a lateral direction, wherein the guide rail primary structure forms a first main load path and the reinforcement structure forms a redundant second main load path.

Abstract: An aircraft wing is provided having a wing leading edge, a wing leading edge slat positioned forwardly of the wing leading edge having an internal duct extending in a spanwise direction of the wing leading edge, a cut-out opening in the wing leading edge, a telescopic tube extending through the cut-out opening and connected to the internal duct of the wing leading edge 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 shuttering mechanism synchronously connected to the telescopic tube to close the cut-out opening in response to the telescopic tube being moved from the retracted condition to the extended condition thereof.

Abstract: An aircraft wing is provided with a positionally fixed closure fairing to close a cut-out opening in the leading edge of the wing associated with a wing leading edge slat so as to direct incident airflow to the wing leading edge from a lower surface of the aircraft wing to an upper surface of the aircraft wing.

Abstract: An aerodynamic laminar flow structure comprises a flow body and a leading edge designed to face a flow circulating in a flow direction, the leading edge being movable and comprising a retracted position in which the edge of each of two flow surfaces of the flow body is joined respectively to an edge of each of two flow surfaces of the leading edge along a parting line having at least one portion inclined at an angle strictly less than 90° relative to the flow direction. The inclination of at least one portion of the parting line makes it possible to reduce drag and thus to retain a laminar flow over a major part of the exterior surfaces of the aerodynamic structure.

Abstract: A tiltrotor controls shield having a blade or wire substructure under a fragile spinner fairing improves bird strike durability. The present disclosure discloses a spinner wind fairing with a shield structure disposed thereunder for providing protection to the proprotor assembly components. The shield structure can segment a projectile, such as a bird, that penetrates the spinner fairing into a series of smaller and lower energy elements spread across a wider area, such that the rotor components can withstand the impact of the smaller elements without damage.

Abstract: Methods and systems for operating an aircraft powerplant comprising an engine coupled to a variable-pitch propeller capable of generating forward and reverse thrust are described herein. A request to enable a mode for automated reverse thrust is received. Reverse thrust conditions are determined to have been met when the aircraft is on-ground, a blade angle of the propeller is below a blade angle threshold and a position of a power lever is at a selected idle region of the power lever. Reverse thrust of the propeller is triggered when the mode for automated reverse thrust is enabled and the reverse thrust conditions have been met.

Abstract: A system and method for actuating one or more high-lift flight control surfaces of an aircraft are disclosed. The system comprises actuators operatively coupled between a driveline and one or more high-lift flight control surfaces associated with a wing of the aircraft. The actuators are configured to cause actuation of the one or more first high-lift flight control surfaces in response to being driven by the first driveline. Each actuator is associated with a no-back device configured to prevent an air load on the one or more high-lift flight control surfaces from driving the one or more high-lift flight control surfaces. The system also comprises a backup brake applicable to the driveline. The backup brake can be applied upon the identification of a developing unsafe condition such as an asymmetry condition between the flight control surfaces of each wing of the aircraft or an uncommanded movement the flight control surfaces.

Abstract: Systems and methods for an Automated Guided Vehicle (AGV) capable of automatically balancing large and heavy objects for transport through a facility. One embodiment is an Automated Guided Vehicle (AGV) including a balancing plate configured to support a load, load sensors configured to detect a weight distribution of the load, and an actuator configured to shift the balancing plate laterally. The AGV also includes a weight balancing controller configured to determine a center of gravity of the load based on the weight distribution detected by the load sensors, to determine that the center of gravity of the load is vertically misaligned with a center of gravity of the AGV, and to direct the actuator to shift the balancing plate laterally to move the center of gravity of the load toward vertical alignment with the center of gravity of the AGV.

Abstract: A system is provided for maximizing efficient ground travel in wide-body and other aircraft equipped with onboard non-engine drive means for autonomous ground travel. Selective operation of the non-engine drive means and selective operation of the aircraft's engines are integrated to power aircraft movement when different ground travel speeds are required between landing and takeoff, optimizing savings and maximizing the cost/benefit ratio for equipping the aircraft with a non-engine drive means. The non-engine drive means may be designed to move a wide-body aircraft at low speeds required for ground maneuvers in a ramp area and to move the aircraft at speeds typically used for pushback, initial forward roll, all start-stop situations, and other low speed ground travel. One or more of the aircraft's engines may be operated to move the aircraft at higher airport taxi speeds.

Abstract: A motor mounted on a drone includes a rotor including a propeller mounting portion with a propeller detachably attached, the rotor being rotatable about a central axis, a stator radially facing the rotor with a gap therebetween, and an auto-balancer capable of automatically correcting dynamic balance of the rotor.

Abstract: A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.

Abstract: A rotorcraft including a pilot control having a sensor that generates pilot control position data, a flight control that controls a flight characteristic of the rotorcraft, a trim system connected to the pilot control and configured to move the pilot control, and a flight control computer (FCC) configured to receive the pilot control position data from the sensor. The FCC executes a first flight control process and generates, according to the first flight control commands, a trim signal indicating a target position for the pilot control and to send the trim signal to the trim system to cause the trim system to attempt to move the pilot control to the target position to reflect a position of the flight control, and to monitor a working state of the trim system and execute a retrim process in response to determining that the trim system has failed.

Abstract: An aircraft having a vertical takeoff and landing flight mode and a forward flight mode. The aircraft includes a fuselage and a dual tiltwing assembly having a vertical lift orientation and a forward thrust orientation relative to the fuselage. The dual tiltwing assembly includes a forward wing and an aft wing coupled together and to the fuselage by a quadrilateral linkage. A distributed propulsion system is coupled to the dual tiltwing assembly and includes a plurality of forward propulsion assemblies coupled to the forward wing and a plurality of aft propulsion assemblies coupled to the aft wing. A flight control system is operably associated with the distributed propulsion system and the dual tiltwing assembly. The flight control system is operable to independently control each of the propulsion assemblies and is operable to transition the dual tiltwing assembly between the vertical lift orientation and the forward thrust orientation.