Abstract: A bicycle rear derailleur is basically provided with a base member including a frame mounting portion having a mounting opening, and a fastening member extending through the mounting opening of the base member. The fastening member has a first threaded portion and a placement portion adjacent to the first threaded portion. An adjusting member is configured to adjust a position of the bicycle rear derailleur relative to a bicycle. An intermediate member includes a contact portion disposed between the adjusting member and the bicycle. The intermediate member has a second threaded portion configured to threadedly engage with the first threaded portion of the fastening member. The second threaded portion has an innermost diameter that is smaller than the outermost diameter of the first threaded portion. The intermediate member is disposed on the placement portion of the fastening member.

Abstract: A bicycle rear derailleur is basically provided with a chain guide and an indicator. The chain guide includes a guide pulley. The indicator is provided on the chain guide such that the indicator disposed on or in an outer periphery of the chain guide. The indicator is indicative of a setting position of an outer circumference of a sprocket of a bicycle rear sprocket assembly relative to the guide pulley.

Abstract: A bicycle gear shifter comprises a shift positioning ratchet provided with a number of positioning teeth, release teeth and drive teeth, a drive member for driving the rotation of the shift positioning ratchet, a mounting member mounted on a bicycle handlebar, a resettable positioning member, a release member for driving movements of the positioning member, a fixing member connected to the mounting member, and an actuating member for driving the shift positioning ratchet to reversely rotate. The shift positioning ratchet and the actuating member are mounted on the fixing member by a rotatable main shaft, the positioning member is sleeved around the rotatable main shaft, and the positioning pawl engages with the positioning teeth. The drive member is sleeved around the rotatable main shaft and is provided with a driving part engaging with the driving teeth.

Abstract: A rotation calculating device comprising: a first rotating device; a first target device; an first optical characteristic acquiring device, configured to acquire optical characteristics for at least one feature of the first target device; and a calculating unit, configured to calculate rotation for the first rotating device based on the optical characteristics of the feature.

Abstract: A sailing vessel is disclosed which comprises a hull, a keel depending from the hull and a mast. A ballast bulb is provided at the lower end of the keel. A first control mechanisms is provided for rotating the ballast bulb about a transverse axis to change the angle of attack of the bulb. A second control mechanism is provided for rotating the bulb about a longitudinal axis of the vessel.

Abstract: Shrouds for water vessels are described herein. In various embodiments, a shroud may include port, starboard, and bow surfaces that are contoured to an outer periphery of one or more inflatable tube portions of an inflatable raft. The shroud may also include a bottom surface from which at least the port side surface and starboard side surface extend upwardly. The shroud may define an interior cavity that is bounded by the port side surface, a starboard side surface, and the bow surface. The interior cavity may be sized and shaped to removably receive the inflatable raft. In some embodiments in which the shroud is secured to a self-bailing raft, the shroud may obstruct one or more fore self-bailing ports of the self-bailing inflatable raft and leave one or more aft self-bailing ports of the self-bailing inflatable raft unobstructed.

Abstract: A method, system, apparatus, and/or device for anchoring a watercraft. The method, system, apparatus, and/or device may include a head and a scissoring shank. The head may be configured to dig into a seafloor of a body of water to restrict the movement of a watercraft. The scissoring shank may be connected to the head. The scissoring shank may include a pivot member connected to the head. The scissoring shank may include a first shank arm connected to the head by the pivot member. The scissoring shank may include a second shank arm connected to the head. The scissoring shank may include a first hole 215 extending through the first shank arm and the second shank arm. The scissoring shank may include a shear member inserted into the first hole. The shear member may restrict the first shank arm from rotating about the pivot member.

Abstract: A continuous vertical tubular handling and hoisting buoyant structure has a hull, a main deck, an upper neck extending downwardly from the main deck, an upper frustoconical side section, an intermediate neck, a lower neck that extends from the intermediate neck, an ellipsoidal keel and a fin-shaped appendage secured to a lower and an outer portion of the exterior of the ellipsoid keel. The upper frustoconical side section is located below the upper neck and maintained to be above a water line for a transport depth and partially below the water line for an operational depth of the buoyant structure. An automated stand building system mounted to the hull is in communication with a controller and configured to make up the marine risers, make up casing, and make up drill pipe.

Abstract: A computing apparatus that is integrated within a flotation module, the system obtaining the energy required to power its computing operations from waves that travel across the surface of a body of water on which the flotation module sets. Additionally, the self-powered computing apparatus employs novel designs to utilize its close proximity to the body of water and/or to strong ocean winds to significantly lower the cost and complexity of cooling their computing circuits.

Abstract: An apparatus for launching, stowing and retrieving of daughter boats (1) from a midships hangar or mission bay on a mother vessel comprises at least one davit assembly positioned atop a stationary cradle (2), located one each near the starboard and port of the mother vessel. The daughter boats (1) are secured on specially designed stationary cradlesalong a plurality of longitudinal tracks (5) and also on at least the two stationary cradles (2) one each near the starboard and port of the mother vessel which are also specially designed and lie along at least one transverse track (6).

Abstract: An Adjustable Fin Assembly for Watercraft. The modular assembly should be design to be incorporated into a surfboard or other watercraft during fabrication of the craft. Each fin assembly is designed to allow for the watercraft user or fabricator to attach a conventional fin element to it. The fin assembly enables the user to adjust the fin position longitudinally as well as laterally relative to the watercraft. The housings each include a set screw or other component that can be loosened and tightened by the user in order to reposition the fin and then fix it in the new position. The conventional fin attaches to a sliding plate that is housed within a housing, wherein the movement of the sliding plate relative to the housing is prevented by engagement with the set screw.

Abstract: A diving snorkel and an upper exhaust head thereof are provided. The upper exhaust head includes a main body and a float. The main body has a recess and an air passage. An upper end of the recess is provided with an air hole communicating with the air passage. A periphery of the air hole is provided with a sealing ring. The recess is provided with a pivot seat thereon. The float is rotatably disposed on the recess. The float has a pivot portion. The pivot portion is pivotally connected to the pivot seat.

Abstract: A snorkel having an elongated inhalation tube with a first end and a second end, the first end of the elongated inhalation tube having an opening that freely admits air flow into the snorkel. The snorkel also has an elbow-shaped conduit with at least one open end removably securable to the second end of the elongated inhalation tube. A mouthpiece is removably securable to the elbow-shaped conduit, wherein the mouthpiece includes a chamber with a middle opening, a left end opening and a right end opening. The snorkel includes a plurality of one-way valves that can direct air and water flow in and out of the snorkel such that only fresh air is breathed in by a user. Additionally, the snorkel has a clip located along the second end of the elongated tube to removably secure the snorkel to a face mask.

Abstract: Systems and methods are provided for underwater use. In one example the system includes an autonomous mother unmanned underwater vehicle (AMUV) and one or more auxiliary unmanned underwater vehicles (UUV). The AMUV is configured for autonomously searching for and detecting undersea objects potentially present in an undersea region of interest (ROI), for generating object information relating to the objects detected thereby to enable identification of at least one object of interest (OOI) among the detected objects, and for selectively transporting the UUV to at least within a predetermined distance from a location of the OOI. The UUV is configured for interacting with the OOI at least within the predetermined distance. Such a system is further configured for providing verification information indicative of the interaction between the UUV and the OOI. The AMUV includes a communications system at least configured for transmitting at one or both of the verification information and the object information.

Abstract: A docking system has flat funnel and a slotted ramp at the end of the flat funnel. The ramp has a plurality of inclined planes, each on a respective side of the slot. A docking adapter, fitted over an underwater vehicle, includes a guide plane and a mask. The funnel guides the guide plane to the top of the ramp during docking/charging of the underwater vehicle. Another aspect of the invention is a highly maneuverable glider including a forwardly mounted buoyancy module followed, in order, by a pitch module, a processing module, and a roll module, mounted concentrically with respect to each other. The glider may be attached to any docking system. When used in conjunction with the docking system of the present invention, the glider may be attached to either the flat funnel or the docking adapter of the docking system of the present invention.

Abstract: A device (100) has surfaces (21, 22, 23, 24) and an anti-biofouling system (10) comprising at least one light source (11, 12) for performing an anti-biofouling action on at least a majority of the surfaces, the at least one light source (11, 12) being adapted to emit rays of anti-biofouling light. The surfaces (21, 22, 23, 24) are configured relative to each other and to the at least one light source (11, 12) such that during operation of the at least one light source, at least a majority of the surfaces (21, 22, 23, 24) is free from shadow with respect to the rays of anti-biofouling light from the at least one light source (11, 12), wherein it may be possible for the rays of anti-biofouling light to reach the surfaces (21, 22, 23, 24) by skimming along the surfaces (21, 22, 23, 24).

Abstract: A recreational power and stabilizing apparatus according to various aspects of the present technology includes an elongated handle body, a spring member coupled to the elongated handle body, and a traction element. The spring member comprises a compound curving element having a lower power region and a high power region. The traction element is coupled to the spring member and engages the ground during use.

Abstract: A paddle mount for a boat is described. The mount includes a generally t-shaped tubular body including a flange and a stem, where the length of the flange and the stem is adjustable and the ends of the flange are configured to rest on opposite sides of the boat cockpit. The mount is configured to couple to the front end of the cockpit and to an end of the stem, such that the t-shaped body may be rotated upwards away from the boat. A mount adapter is also described that may be used to attach a paddle to the boat using the mount.

Abstract: A quarter-twist pedal propeller includes a propeller blade and a support frame. A large synchronous wheel is mounted on an upper part of the support frame through a main shaft, a pedal assembly is mounted on each end of the main shaft. A small synchronous wheel is mounted on a lower part of the support frame through a secondary shaft. A waterproof plate is mounted outside the support frame. The waterproof plate is disposed above the propeller blade. A portable cover that covers the large synchronous wheel is provided on top of the support frame. A grabbing part is provided on the portable cover. A balancing pole is transversely connected to the portable cover. The present invention is practical and cost-effective, has novel and simplified structure, and can reduce power loss due to multiple transmissions. It is convenient during pedaling.

Abstract: A V-hull boat design having the engine placed forward of the longitudinal centerline offers advantages over traditional boat designs. The engine is placed forward of the longitudinal centerline of the boat and under the walking deck within the passenger cabin such that it does not interfere with the placement of passenger seating within the boat. Placement of the engine in a position forward of the longitudinal centerline of the boat moves the center of gravity of the boat forward compared with traditional I/O, V drives, and direct drives. By placing the engine forward of the longitudinal centerline, in a location that is generally not utilized in the hull of the boat, substantial passenger and cargo room is preserved in the aft half of the boat. Bow rise during acceleration is reduced; ride comfort is improved through chop or waves; and wake performance behind the boat is improved.

Abstract: According to an example aspect of the present invention, there is provided a steering system of an azimuthing propulsion system, the steering system comprising at least one hydraulic motor configured to operate an azimuthing system of a propulsion unit, the propulsion unit being arranged outside a vessel, a fluid cycle from the at least one hydraulic motor via a separate hydraulic overload protection unit and back to the motor, the overload protection unit comprises a pressure relief unit and a heat management unit, and wherein the pressure relief unit comprises a pressure relief valve, and the heat management unit comprises a heat storage, a heat exchanger, or a combination of both, and wherein the fluid cycle comprising the overload protection unit is configured to at least partially absorb heat generated during turning of the propulsion unit.

Abstract: A propulsion device for a ship capable of preventing idling of a propeller without any limitation on the type of clutch. The propulsion device includes: a forward and reverse switching clutch (17) for transmitting the driving power from an input shaft (11) to a forward gear (13A) or a reverse gear (13B); a forward one-way clutch (18A), disposed between the input shaft (11) and the forward gear (13A), for connecting the forward gear (13A) and the input shaft (11) when the forward gear (13A) is rotated at a higher speed than that of the input shaft (11); and a reverse one-way clutch (18B), disposed between the input shaft (11) and the reverse gear (13B), for connecting the reverse gear (13B) and the input shaft (11) when the reverse gear (13B) is rotated at a higher speed than that of the input shaft (11).

Abstract: The proposed design is of a generally spherical, semi-spherical, cone-shaped, or bell-shaped mini-autonomous airship that has an internal guidance and control system connected to ground operations. The structure of the airship is approximately 2.25 ft in diameter and 2.625 ft in height with a double layered ballonet structure and a gondola on the bottom housing the propulsion, guidance, control, sensor, and communication systems. This unique mini-airship serves to provide persistent low-altitude low-cost surveillance. The airship has a propulsion and control system that permits it to rise over a desired loitering location, and to be maintained in that location for a period of time. In one embodiment the airship may achieve neutral buoyancy when the internal envelope is about 60% full of lifting gas, and may have a service ceiling of about 100 meters. The airship has an equipment module that can include either communications equipment, or monitoring equipment, or both.

Abstract: A stringer for having a runout with a raised area configured to reduces stress while improving drainage across the runout when utilized in a close structural component of a vehicle such as an aileron of an aircraft. In one or more configurations, the raised area of the runout of the stringer includes multiple tapered surfaces adjacent to one another oriented and configured as ramps to collectively guide water up, over and down the raised area of the stringer.

Abstract: An aerial vehicle having an arm for supporting an a lift generating means, the aerial vehicle being advantageously a multicopter, comprising an arm mount means for swinging an arm supporting the lift generating means between a retracted position and an extended locked and releasable position.

Abstract: A composite assembly includes a composite skin which includes a plurality of composite plies and a composite stringer secured to the composite skin. A first composite plank ply is positioned between a first pair of composite plies of the plurality of composite plies of the composite skin; the first composite plank ply has a width dimension less than a width dimension of the plurality of composite plies of the composite skin; and the first composite plank ply extends along a length of the composite stringer. At least a portion of the composite stringer is positioned in overlying relationship with the first composite plank ply.

Abstract: A box structural arrangement (1) for an aircraft including first (2) and second composite layers (3), at least one spar web (4) extended between opposite edges of the first and second composite layers (2, 3) along a longitudinal direction, and a conduit piece (5) extended between opposite edges of the first and second composite layers (2, 3). The conduit piece (5) has a hollow section (6) comprising at least one conduit (7) dimensioned to receive pipes or harnesses and surrounded by a resilient material (8). The conduit piece (5) is mounted on the spar web (4) to provide a channeled box structural arrangement (1). The box structural arrangement can be applicable in a torsion box or a wing. The invention further refers to a method for manufacturing the box structural arrangement for an aircraft.

Abstract: An apparatus includes a first composite support structure and a second composite support structure. The first and second composite support structures are in a predetermined position relative to one another. The apparatus further includes an uncured pre-preg ply, wherein: the uncured pre-preg ply overlies at least a portion of the first composite support structure; the uncured pre-preg ply overlies at least a portion of the second composite support structure; and the first and second composite support structures are each stiffer than the uncured pre-preg ply.

Abstract: Integrated slat chine apparatus and methods are described. An example apparatus includes a chine and a slat. The chine is coupled to an airfoil. The chine includes a lateral surface. The slat is located adjacent the lateral surface of the chine and coupled to the airfoil. The slat is movable relative to the airfoil between a stowed position and a deployed position. The slat is to expose the lateral surface of the chine when the slat is in the deployed position and to cover the lateral surface of the chine when the slat is in the stowed position.

Abstract: A propeller component, for example a propeller blade airfoil, comprises an external surface exposed in use to an oncoming airstream (A), and a protective polymeric film applied over substantially the entire exposed external surface of the component.

Abstract: A mechanism for folding a rotor blade that is rotatably coupled to a blade cuff about a blade-fold axis between an extended position and a folded position. The mechanism includes a swash plate configured to translate relative to a mast, a pitch link rotatably coupled to the swash plate, a pitch horn rotatably coupled to the pitch link, a crank coupled to the pitch horn, and a link rotatably coupled to the crank and rotatably coupled to the rotor blade. The pitch horn and the crank being configured to commonly rotate relative to the blade cuff about a crank axis in response to translation of the swash plate, wherein the crank axis passes through the blade cuff.

Abstract: An actuator is disclosed comprising: a moveable member; a first hydraulic chamber in contact with a first surface of the moveable member; a second hydraulic chamber in contact with a second, opposing surface of the moveable member; a movable locking mechanism coupled to a moveable wall of the second hydraulic chamber; and a resilient biasing member acting on the moveable wall of the second hydraulic chamber so as to bias the moveable wall and locking mechanism. The actuator is configured to selectively vary the pressure in the second hydraulic chamber so that the resilient biasing member is able to bias the moveable wall to move, thereby moving the locking mechanism to engage the moveable member so as to prevent the movement of the moveable member towards at least one of the first and second hydraulic chambers.

Abstract: A system and method for providing state comparison of redundant processors used, e.g. to control a rotor craft. A primary microprocessor is configured to receive input data from a position sensor and a flight condition sensor and determine therefrom a first desired control law state, and a secondary microprocessor is configured to receive input data from the position sensor and the flight condition sensor and determine therefrom a second desired control law state. The first desired control law state from the primary microprocessor and the second desired control law state from the secondary microprocessor are compared, and (a) the first desired control law state is entered when the first desired control law state and the second desired control law state match, and (b) a last known control law state is maintained when the first desired control law state and the second desired control law state do not match.

Abstract: A leading edge structure (1) for a flow control system of an aircraft, including a double-walled leading edge panel (3) that surrounds a plenum (7), wherein the leading edge panel (3) includes an inner wall element (21) facing the plenum (7) and an outer wall element (23) in contact with the ambient flow (25), wherein between the inner and outer wall elements (21, 23) the leading edge panel (3) includes elongate stiffeners (27) spaced apart from one another, so that between each pair of adjacent stiffeners (27) a hollow chamber (29) is formed between the inner and outer wall elements (21, 23), wherein the outer wall element (23) includes micro pores (31) forming a fluid connection between the hollow chambers (29) and an ambient flow (25), and wherein the inner wall element (21) includes openings (33) forming a fluid connection between the hollow chambers (29) and the plenum (7).

Abstract: An aircraft assembly having: a first part; a second part, the first part being movably mounted relative to a second part; a dynamic conduit arranged such that movement of the first part relative to the second part causes the dynamic conduit to move through a movement volume from a first conduit position to a second conduit position; a first fastener arranged to couple a component to the aircraft assembly, at least some of the first fastener residing within the movement volume of the dynamic conduit; and a safety guide arranged to be coupled to the first fastener, the safety guide comprising a bridge portion which extends away from the first fastener within the movement volume of the dynamic conduit so as to support the dynamic conduit when the dynamic conduit is in the second conduit position.

Abstract: A powered clutch assembly is provided for an aircraft landing gear or other vehicle wheel drive system equipped with wheel drive motors controllable to move the aircraft or vehicle during ground travel. Electric power for the clutch assembly is transferred to clutch actuation elements by a rotary power transfer assembly mounted between stationary and rotating elements within the landing gear wheel drive system to clutch actuation elements. Actuation elements are powered to securely lock clutch rotating elements when required to improve the reliability of failsafe operation of the clutch assembly when torque should not be transferred and to unlock clutch rotating elements when torque should be transferred when the landing gear wheel drive system is used to drive the aircraft during ground travel. Power transferred from the rotary power transfer assembly may also be used to operate components associated with the aircraft drive wheel other than the powered clutch assembly.

Abstract: A damper is provided for responding to relative movement of arms to which the damper is coupled. The damper includes a member, springs, a first housing and a second housing. The first housing includes a first body and first bellows affixed to the member and the first body by first joints to define a first interior. The second housing includes a second body and second bellows affixed to the member and the second body by second joints to define a second interior. The first and second interiors are configured to contain fluid charged therein and the member is configured to permit bi-directional flows of the fluid between the first and second interiors responsive to the relative movement of the arms and in opposition to an elasticity of the springs.

Abstract: A float has a front-to-back length, a width, and a height where the front-to-back length of the float is strictly greater than the height of the float which in turn is strictly greater than the width of the float. At least a bottom portion of the float is watertight. The float includes an access panel to access the inside of the float. A battery is inside the float and is accessible via the access panel.

Abstract: As one aspect of this multicopter, the multicopter flies on the basis of information from a flight controller and is provided with the following: a main body section; a plurality of propulsion units having rotating rotary wing, the propulsion units being attached to the main body section; motors installed in the main body section or the propulsion units; at least one first detection unit that detects motor information; and a wireless transmission unit that wirelessly transmits, to the outside, the motor information detected by the first detection unit.

Abstract: A vertical takeoff and flying at a constant altitude are performed using an aircraft. The aircraft includes a fuselage, a left arm (attached to the fuselage), a right arm (attached to the fuselage), a left float (attached to the left arm), a right float (attached to the right arm), and a plurality of rotors. The plurality of rotors includes a left inner rotor and a right inner rotor (attached at a fixed angle to a top surface of the left float and the right float, respectively) and a left outer rotor and a right outer rotor (attached at a fixed angle to a top surface of the distal end of the left arm and the right arm, respectively).

Abstract: A variable-speed gearbox for a tiltrotor with fixed engine and rotating proprotor includes an input shaft coupled to the respective fixed engine, an output shaft coupled to the respective proprotor; a high-speed clutch integrated into a high-speed gear train, the high-speed gear train having an input coupled to the input shaft and an output coupled to the output shaft; and a low-speed clutch integrated into a low-speed gear train, the low-speed gear train having an input coupled to the input shaft and an output coupled to the output shaft. The high-speed clutch and the low-speed clutch can be freewheeling clutches capable of disconnecting the output and the input of the respective gear train of the high and low-speed gear trains in an overrunning condition when the output rotates faster than the input of the respective gear train. The low-speed clutch can be permanently engaged. In accordance to some embodiments the variable-speed gearboxes may include an accessory drive.

Abstract: A shrouded rotor assembly for an aircraft. The shrouded rotor assembly comprises a stator hollow structure comprises formed from a plurality of composite angular segments. Each composite angular segment includes: a core arched section of a central hub casing, a peripheral rim section of an external hollow duct and a pair of angularly opposed sliced portions, respectively for one of a pair of guide vanes. The resulting stator hollow structure is a unitary one-piece, integrating together continuously the composite angular segments. The invention typically applies e.g. to aircrafts such as rotary wing aircrafts.

Abstract: The present invention relates generally to a vertical take-off and landing (VTOL) aircraft and a propulsion system for a vehicle vertical take-off and landing (VTOL), for example, helicopters, others VTOL aircrafts. The claimed VTOL aircraft provides a most effective control of the aircraft equipped with such a propulsion system, performed through the optimal distribution of the airflow generated by the rotor, while maintaining the simplicity, reliability and efficiency of the aircraft design.

Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a yoke having a plurality of blade arms with inboard pockets. A centrifugal force and shear bearing assembly is disposed in each of the inboard pockets of the yoke. Each of a plurality of proprotor blades is coupled to the yoke by one of the bearing assemblies such that each proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point. Each bearing assembly includes a centrifugal force bearing coupled to the yoke, a shear bearing coupled to the yoke and an inboard beam coupled between the centrifugal force bearing and the shear bearing. Each inboard beam is coupled to a respective proprotor blade.

Abstract: A proprotor system for a tiltrotor aircraft includes a yoke having a plurality of blade arms each having an inboard pocket. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets. Each of a plurality of inboard beams is disposed at least partially between a centrifugal force bearing and a shear bearing of each bearing assembly and has a proprotor blade coupled thereto. Each of a plurality of latch assemblies selectively couples one of the bearing assemblies to the yoke. Each latch assembly is rotatable relative to the yoke between an engaged position wherein the latch assembly is engagable with one of the bearing assemblies to couple the bearing assembly to the yoke and a disengaged position wherein the latch assembly is disengaged from the respective bearing assembly enabling installation and removal of the respective bearing assembly relative to the respective pocket.

Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode includes a yoke having a plurality of blade arms each having an inboard pocket with a load transfer surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets. Each of a plurality of inboard beams is disposed at least partially between a centrifugal force bearing and a shear bearing of each bearing assembly and has a proprotor blade coupled thereto. Each of a plurality of independent shoes is coupled between one of the centrifugal force bearings and the yoke. Each shoe has a load transfer surface that has a contact relationship with the load transfer surface of the respective inboard pocket forming a centrifugal force load path therebetween.

Abstract: A proprotor system for a tiltrotor aircraft having helicopter and airplane flight modes includes a yoke having a plurality of blade arms each having an inboard pocket with an outboard surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets with each bearing assembly including a shear bearing and a centrifugal force bearing having an integral shoe with an outboard surface. Each of a plurality of inboard beams is disposed at least partially between one of the centrifugal force bearings and one of the shear bearings. Each of a plurality of proprotor blades is coupled to one of the inboard beams. The integral shoes are coupled to the yoke such that there is a spaced apart relationship between the outboard surfaces of the integral shoes and the outboard surfaces of the pockets to prevent centrifugal force load transfer therebetween.

Abstract: A proprotor system for a tiltrotor aircraft having helicopter and airplane flight modes includes a yoke having a plurality of blade arms each having an inboard pocket. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets with each bearing assembly including a bearing cage, a shear bearing and a centrifugal force bearing. Each of a plurality of inboard beams is disposed at least partially between one of the centrifugal force bearings and one of the shear bearings. Each of a plurality of proprotor blades is coupled to one of the inboard beams. Hub bolts couple each of the bearing cages to the yoke such that the hub bolts provide centrifugal force load paths between the bearing assemblies and the yoke inboard of the inboard pockets.

Abstract: Systems, methods, and devices provide a vehicle, such as an aircraft, with rotors configured to function as a tri-copter for vertical takeoff and landing (“VTOL”) and a fixed-wing vehicle for forward flight. One rotor may be mounted at a front of the vehicle fuselage on a hinged structure controlled by an actuator to tilt from horizontal to vertical positions. Two additional rotors may be mounted on the horizontal surface of the vehicle tail structure with rotor axes oriented vertically to the fuselage. For forward flight of the vehicle, the front rotor may be rotated down such that the front rotor axis may be oriented horizontally along the fuselage and the front rotor may act as a propeller. For vertical flight, the front rotor may be rotated up such that the front rotor axis may be oriented vertically to the fuselage, while the tail rotors may be activated.

Abstract: Disclosed herein are unmanned aerial vehicles (UAVs). Some UAVs include a vertically-mounted printed circuit board (PCB). The UAVs have yaw, pitch, and roll axes. The UAVs comprise a plurality of propellers, each of the plurality of propellers configured to rotate about a respective one of a plurality of axes of rotation; a base assembly coupled to each of the plurality of propellers; and a PCB coupled to the base assembly. A surface of the PCB lies in a plane defined by the yaw axis and the roll axis, and no portion of the PCB intersects any axis of rotation of any propeller of the unmanned aerial vehicle. The PCB may have a non-rectangular shape, such as the shape of a shark. Some UAVs include a PCB comprising a mechanical feature configured to engage with a peripheral or a peripheral subassembly.