Abstract: A modular counterweight system includes a housing, a bracket, and an actuator. The housing is configured to selectively interface with a plurality of counterweights, facilitating incremental adjustment of an overall weight of the modular counterweight system. The bracket is configured to couple the housing to the vehicle, and the housing is at least one of (i) pivotally coupled to the bracket, (ii) extensionally coupled to the bracket, and (iii) translationally coupled to the bracket. The actuator is positioned to selectively reconfigure at least one of the housing and the bracket and thereby change the center of gravity of the modular counterweight system.

Abstract: The present application describes apparatus for attaching or securing a fifth wheel hitch to a bed of a towing vehicle. The fifth wheel hitch may be arranged to be secured to a hitch ball, such as a gooseneck hitch ball. The fifth wheel hitch may include a chamber for accepting a hitch ball, a locking pin for securing the hitch ball in the chamber, and a handle for selectively securing and releasing the hitch ball. The locking pin may be biased towards a position for securing the hitch ball in the chamber. A damper may be included to dampen impact forces transferred from the trailer to the towing vehicle through the fifth wheel hitch. The fifth wheel hitch may include support members having wear strips that may rest on the surface of the towing vehicle bed.

Abstract: A robotic vehicle includes a chassis, a cabin, a driving device, a plurality of detection devices, and a control device. The cabin is installed in the upper portion of the chassis. The driving device is positioned on the chassis for moving the robotic vehicle and rotating the cabin. A plurality of detection devices and a control device are installed for reconnoitering an area. The two sides of the chassis are coupled to track wheels, and a front portion of the chassis is coupled to a climbing support mechanism.

Abstract: The method is for producing a bus using a cutaway van chassis, the bus being of the type having a sliding passenger door and the chassis being of the type having a passenger door frame including a horizontal rail, an A-pillar extending to the rail and a B pillar extending to the rail, the A-pillar being adapted to receive a swinging door. In the method, the B-pillar and the rail are removed to produce a modified chassis and the remainder of the bus is constructed about the modified chassis.

Abstract: A bracket for attachment to an elongate member, comprising an inner portion, the inner surface of which conforms, in use, to an outer surface of the elongate member, said elongate member defining a longitudinal axis and an outer portion comprising a clamping means operable to clamp the outer portion to the inner portion such that the outer portion at least partially surrounds the inner portion, wherein the inner portion is shaped such that, in use, the outer portion may be clamped to the inner portion at a plurality of orientations about an axis orthogonal to the longitudinal axis.

Abstract: A cable arranging system is provided for being arranged on a frame of a bicycle, the frame has an axial tube portion and a handle portion, the axial tube portion includes a head tube and a front standing tube disposed through the head tube and rotatable relative to the head tube, the handle portion and the front standing tube are connected with each other and rotatably comovable, the handle portion is rotatable about the head tube and has an operating portion positionably arranged thereto; and the cable arranging system includes a first steering portion positionably assembled to the axial tube portion, and at least one controlling cable. The at least one controlling cable is for being connected with the operating portion and connected to an actuating mechanism of the bicycle, and each said controlling cable is controllably driven by the operating portion.

Abstract: A scooter having a riding platform rotationally engaged to a front steering assembly is provided which significantly increases the ability of riders to perform tricks. The riding platform is rotationally engaged to the steering column which itself may be employed as a riding platform. An optional mechanism may be employed whereby the riding platform is rotated by a spin of the steering column with the handlebars. The scooter may also be equipped with skids to allow employment in the snow or on ice.

Abstract: A hydraulic disc brake device includes a cover, a hydraulic unit, an oil tube and a disc brake unit. The cover includes at least one accommodating space, at least one oil route, a proximal end and a distal end. The distal end towards a moving direction of the bicycle. The hydraulic unit includes a hydraulic cylinder and a piston. The hydraulic cylinder is assembled in the accommodating space. The piston is assembled in the hydraulic cylinder for controlling a pressure of the oil route. The disc brake unit is connected with the oil tube and controlled by a pressure of the oil tube.

Abstract: An elliptical drive mechanism and a steering mechanism, applicable to velocipedes in general, is disclosed. Sliding blocks are capable of sliding along guide rods such that the sliding blocks are movable along the guide rods in an elliptical trajectory while the sliding blocks are simultaneously capable of driving cranks to cause a chain to drive a ratchet for driving a rear wheel. A steering mechanism for velocipedes in general is disclosed. The steering mechanism allows leftward or rightward movement of the handlebar to produce rotation of the rear wheel fork and corresponding turning of the rear wheel.

Abstract: A bicycle drive unit basically has a transmission, a motor and a resultant force member. The motor is configured to transmit rotation to the transmission, and a resultant force member to which rotation from the transmission and from the manual drive force is transmitted. The transmission has a first sun gear, a second sun gear, a first ring gear, a second ring gear, a first planetary gear, a second planetary gear and a third planetary gear. The first, second and third planetary gears are separate individual gears. The first planetary gear is engaged with the first sun gear and the first ring gear. The second planetary gear is engaged with the second sun gear and the third planetary gear. The third planetary gear is engaged with the second planetary gear and the second ring gear.

Abstract: A bicycle drive unit includes a first planetary gear mechanism, a first motor, a second motor and a resultant force member. The first planetary gear mechanism includes a first input body, a first output body and a first transmission body that transmits the rotation of the first input body to the first output body. The first motor is configured to rotate the first input body. The second motor is configured to rotate the first transmission body. The resultant force member is selectively rotated by the rotation of the first output body and by a manual drive force without interposing the first planetary gear mechanism.

Abstract: A bicycle drive unit includes a housing, an output unit, a first motor and a second motor. The housing rotatably support a crankshaft. The output unit is provided in the housing and to which rotation of the crankshaft is transmitted. The first motor is provided in the housing that can assist a manual drive force without changing the ratio of the rotational speed of the output unit relative to the rotational speed of the crankshaft. The second motor is provided in the housing to assist the manual drive force without changing the ratio of the rotational speed of the output unit relative to the rotational speed of the crankshaft.

Abstract: A bicycle drive unit is provided that basically includes a planetary gear mechanism, a first motor and a worm drive. The planetary gear mechanism includes an input body, an output body and transmission body. The input body is configured to receive rotation from a crankshaft. The output body is configured to output rotation from the input body to outside of the bicycle drive unit. The transmission body is configured to control a rotation ratio of the input body to the output body. The first motor is configured to transmit rotation to the transmission body. The worm drive is provided in a transmission path that transmits rotation between the first motor and the transmission body.

Abstract: A wake adjustment system for a boat may include a wake adjustment device mountable at the stern of the boat to deflect water moving past a stern trailing edge of the boat's running surface. The wake adjustment device includes water deflectors that are rotatable about a first pivot axis for varying a degree of wake adjustment. The wake adjustment device is mounted to the boat proximal to the centerline.

Abstract: A foldaway balcony that includes a vertical support, a platform structure tiltably mounted to the vertical support and a barrier structure mounted on the platform structure. The platform structure includes a support structure and a floor structure which are tiltable separately from one another relative to the vertical support. The barrier structure includes barrier elements, hinged at the edge of the platform structure, and tiltable between a stowed position in which they lie inside the support structure, and a deployed position, in which they stand up relative to the support structure. A barrier element, connected to a distal side of the edge of the platform structure includes a first and a second pair of stanchions hinged to the distal side, a first and a second rod which interconnect the upper ends of the stanchions, and a handrail with parallel guides, in which are housed the first and the second rods.

Abstract: A device capable of immediately locking and releasing a rope without pressing a switch includes two side plates connected with each other to form a case having an internal space. The case has a communication section for a rope to access the case. The case includes: an abutment section fixedly disposed on inner face of one of the side plates; a rotatable cam pivotally disposed on inner face of one of the side plates corresponding to the abutment section, the rotatable cam having an engagement surface and a first linking section; a first elastic body disposed between the side plate and the cam; a rotatable actuation section pivotally disposed on inner face of one of the side plates corresponding to one end of the cam, one end of the actuation section having a second linking section; and a second elastic body disposed between the side plate and the actuation section.

Abstract: A system and method for guiding a dropped suspended load includes a safety winch, safety buoy, and safety anchor spaced relative to one another and an offshore rig's lifting system so that the dropped load falls away from certain seabed locations and to a safe landing area. A safety winch cable runs from the safety winch to the safety buoy, and from the safety buoy to a connection to the load. The load, when in a run-away state, falls away from vertical and toward a predetermined safe landing spot on the seabed floor. The safety buoy is then used to located the load.

Abstract: A handling apparatus (10) for supporting and deploying an object (12), such as a marine craft, comprises a support frame (18) and a cradle (20) upon which the object (12) to be deployed is disposed. A retaining flap (24) forms a first portion of the cradle (20) and is coupled to a deployment ramp (26) which forms a second portion of the cradle (20), the retaining flap (24) being movable between a first position which retains the object (12) on the cradle (20) and a second position in which the object (12) is released for movement relative to the cradle (20). The handling apparatus (10) is movable from a first, storage, position to a second, deployment, position in which the object (12) can be deployed.

Abstract: Lightweight vessel with a kart-like appearance of the type consisting of a lightweight vessel shell, the deadworks thereof being built with all the additions of a kart, the vessel being essentially characterized in that it consists of a shell of a light vessel (1), in the middle part of which there is a propulsion motor (2) which transmits the power to the driving means (4) via transmission means (3), the deadworks consisting of an assembly of elements that form part of the aesthetics of a competition kart, especially consisting of an aerodynamic seat (6) surrounded by aerodynamic side panels (12), an aerodynamic front panel (17), an aerodynamic rear panel, and four wheels (14) with the corresponding mudguards (15) thereof.

Abstract: A collar assembly for a watercraft includes an elongate tubular casing with a lengthwise sealable opening. A foam core is removably positioned in the tubular casing, and includes a body portion and a plurality of circumferentially spaced foam springs that extend outwardly to engage the tubular casing, to bias the foam core towards a center position in the tubular casing. In some embodiments a body portion of the foam core has a circular cross section, and the foam springs are co-formed with the body portion. In some embodiments the foam core comprises a plurality of longitudinal sections that are enclosed in a membrane having an inflation valve that extends through the tubular casing.

Abstract: A device for sealing an opening in a wall includes at least one flexible, deformable balloon; a locking means, which is a bar that is slidable into the opening of the wall from one side of the latter and engages with the opposite side of said wall; a bearing means that is a circular plate capable of bearing on the at least one balloon and of sandwiching same against the wall; and a connection means, which is a flexible rope located between the locking means and the bearing means, passes through an inner duct of the balloon, and is capable of compressing the balloon against the opening.

Abstract: This disclosure provides a protective diving system for isolating a diver from a hazardous diving environment. The protective diving system can include a dry suit system including a dry suit and a surface exhaust valve coupled to the dry suit, and a return-surface exhaust assembly configured to exhaust gas from the dry suit system to a breathable atmosphere outside of the diving environment of the diver. The surface exhaust valve is configured to receive gas from the dry suit and exhaust gas to the return-surface exhaust assembly without exhausting to the surrounding diving environment. The protective diving system can further include one or more chemically-resistant components, where the chemically-resistant components include a fluoroelastomer.

Abstract: Apparatuses, systems, and methods for the deployment of a plurality of seismic autonomous underwater vehicles (AUVs) on or near the seabed. In one embodiment, the AUV comprises a buoyant body coupled to a pressure vessel that contains substantially all of the AUV's electronic components. The pressure vessel may comprise a plurality of composite components coupled together by a metallic ring to provide a substantially cylindrical shape to the pressure vessel. The AUV body provides lift to the AUV during lateral movement and compensates for an overall negative buoyancy of the AUV. The AUV may include a plurality of thrusters for propulsion. A vertical thruster may be used to create an upwards attack angle during takeoff and to maintain depth and orientation during flight. During normal flight operations, the AUV is configured to travel horizontally and vertically in a body of water by using only the horizontal thrusters.

Abstract: A thruster assembly is provided for a marine vessel, the assembly having a propeller unit (14), a motor (10) and a drive shaft (12) linking the motor (10) with the propeller unit (14) to drive the propeller unit (14). The drive shaft (12) is foldable and defines a drive path between the motor (10) and the propeller unit (14). A housing (2) locates the propeller unit (14) in a storage configuration. The motor (10) is fixed with respect to the housing (2), the housing (2) being adapted to be fixed with respect to an opening in a hull (8) of the marine vessel. An actuator (22) is operable to move the propeller unit (14) from the storage configuration to a deployment configuration in a direction from inboard to outboard, the propeller unit (14) being extended from the hull (8) for use in the deployment configuration. The propeller unit (14) is supported by a support assembly (36) which is pivotable relative to the housing (2) about a pivot axis (A).

Abstract: A system for providing marine propulsion is provided including an input shaft driven by a prime mover, a pinion gear coupled to the input shaft, a plurality of planet gears coupled to the pinion gear, a planet carrier having the plurality of planet gears rotationally mounted thereto, and a ring gear surrounding the planet gears and coupled thereto. The planet carrier and ring gear are coupled to internal and external output shafts that are coaxially aligned, which are coupled to aft and forward propulsor elements. The ring gear and planet carrier rotate in opposite directions to provide contra-rotating forward and aft propulsor elements. The ring gear and planet gear are each coupled to rotation altering devices that, when at least one is activated, the rotation of both the planet carrier and ring gear will be altered, thereby altering the rotation of the propulsor elements.

Abstract: A thruster assembly that in addition to propulsion provides water flow to/from compartments and systems on board a vessel. In a first position, the thruster assembly provides propulsion/steering. Pivoted to a second position, operation of the thruster in a first direction draws a flow into the vessel and in a second direction draws a flow out of the vessel. The flows may be conveyed to/from compartments/systems on board the vessel via conduits in communication with a chamber having an opening through which the thruster drives the flows. The flows may be used to submerge/surface the vessel, or to provide systems cooling or serve other functions. Pivoted to a third position the thruster assembly is retracted and enclosed within the chamber to form a hydrodynamically clean exterior.

Abstract: In an outboard motor, a feed passage, through which a lubricating oil that flows upward from a gear mechanism due to rotation of the gear mechanism is fed upward from a gear chamber, includes a first feed passage, extending from the gear chamber to a connection passage via a first upstream passage, a spiral passage, and an interior of an upper bearing, in that order, and a second feed passage, extending from the first upstream passage to the connection passage while bypassing the spiral passage via a bypass passage. The bypass passage is positioned farther outward than the spiral passage in a radial direction of the driveshaft. A diameter of a cross section of the bypass passage that is orthogonal or substantially orthogonal to a center line of the driveshaft is smaller than a maximum diameter of the driveshaft.

Abstract: A boat maneuvering control method for a boat includes setting a target boat speed, detecting an actual boat speed of the boat, and acquiring a base engine rotational speed associated with the target boat speed that is set, correcting the base engine rotational speed according to a difference between the target boat speed and the actual boat speed so as to set the base engine rotational speed that is corrected as a target engine rotational speed, and controlling an engine based on the target engine rotational speed that is set such that the actual boat speed approaches the target boat speed.

Abstract: Provided is a buoyant aerial vehicle which can secure high safety by reducing the risk of crashing, and which can facilitate control of movement by suppressing the influence of wind and exhibit high mobility capability. The buoyant aerial vehicle is configured by including: a buoyant vehicle body in which gas having a specific gravity smaller than air is hermetically filled; a vertical propulsion propeller which provides vertical propulsive force to the buoyant vehicle body; and a horizontal propulsion propeller which provides horizontal propulsive force to the buoyant vehicle body, and is configured such that the buoyant vehicle body has horizontal wind passages formed in at least two directions, and has outer peripheral edges each formed into an acute angle in side view.

Abstract: An aircraft interior lining component is formed at least partially of a thermoplastic foam material and includes a first surface which faces an interior of an aircraft cabin when the aircraft interior lining component is mounted in an aircraft, and a second surface which faces away from the interior of the aircraft cabin when the aircraft interior lining component is mounted in an aircraft. The second surface of the aircraft interior lining component includes at least one supporting section and at least one surface section adjacent to the supporting section and recessed relative to the supporting section. The supporting section is dimensioned and arranged so that it is supported, when the aircraft interior lining component is mounted in an aircraft, on an element of a primary structure of the aircraft at least when a predetermined load acts on the first surface of the aircraft interior lining component.

Abstract: In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.

Abstract: A pressure bulkhead for an aircraft fuselage having a skin element, with a first surface and a second surface, a circumferential edge and a center axis, and a reinforcement assembly, which has radially disposed reinforcement elements extending along the first surface radially between an outer end at the edge of the skin element and an inner end, which faces the center axis, wherein, in a cross section, which extends radially along the center axis, each of the radially disposed reinforcement elements defines first and second contour lines, each extending from the outer end of the radially disposed reinforcement elements to the inner end thereof, and the reinforcement assembly resting with the first contour lines thereof on the first surface of the skin element. A pressure bulkhead for an aircraft fuselage can efficiently absorb occurring pressure loads.

Abstract: An aircraft having an airframe including a hollow structure referred to as a “storage” structure, the storage structure having an opening that is open to the outside of the aircraft. A sealing device extends around the opening, the sealing device including at least one compressible gasket. A plurality of non-removable fittings are fastened to the storage structure. At least one removable storage shell comprises at least a covering configured to close the opening while compressing each gasket. Removable fittings of the storage shell are attached in reversible manner to the non-removable fittings by respective elongate fasteners passing through each removable fitting and the non-removable fitting.

Abstract: An aircraft includes a passenger cabin having a floor, a cargo compartment below the floor, a first access unit for accessing the cargo compartment from the passenger cabin, the first access unit being located on the floor and a utility space module arranged in the cargo. At least one part of the cargo compartment includes a first lateral half and a second lateral half in relation to a longitudinal axis of the aircraft; the lateral halves form the part of the cargo compartment. The utility space module includes a utility space cross-section in a direction normal to the longitudinal axis, which is dimensioned such that it conforms to a cross-section of one of the lateral halves of the cargo compartment. Further, the utility space module is placed exclusively in the first lateral half or the second lateral half of the cargo compartment directly below the first access unit.

Abstract: An aircraft wing is disclosed having a wing tip device configurable between a flight configuration for use during flight and a ground configuration for use during ground-based operations to reduce the span. The wing includes an actuator and an actuation assembly having an articulation mechanism having a master bell crank connected to the actuator and a slave link connecting the master bell crank with the wing tip device. The slave link is pivoted, at one end, to the master bell crank about a first pivot, and at the other end, to the wing tip device about a second pivot. The master bell crank being pivotably mounted, at its base, about a third pivot.

Abstract: An aircraft wing having a wing tip device at the tip thereof is disclosed. The wing tip device is configurable between: a flight configuration for use during flight and a ground configuration for use during ground-based operations to reduce span. In the flight configuration, flight loads may be transferred via a load transfer arrangement from the wing tip device into the fixed wing, but during movement of the wing tip device towards the ground configuration, the load transfer arrangement is disengaged. The wing includes an actuation assembly having a sliding chassis coupled to the wing tip device, via a track and follower arrangement. The track includes a wide portion and a narrow portion.

Abstract: A foldable wing for an aircraft includes a base wing having a base wing end region, a wing tip having a connection region, a first engagement means integrated into the base wing, a second engagement means integrated into the wing tip, and a drive mechanism coupled with the wing tip for moving the wing tip relative to the base wing. The first and second engagement means are adapted for engaging each other along a sliding course from a first position, in which the connection region of the wing tip and the base wing end region are in a flush contact to form a continuous wing, up to a second position, in which the first engagement means and the second engagement means disengage. The drive mechanism includes a first movement element and a second movement element at least partially extending in a spanwise direction, and supported in a linear guide each.

Abstract: According to one embodiment, a flight control system includes a pilot control assembly and a flight control computer. The pilot control assembly can receive commands from a pilot. The flight control computer can receive, from the pilot control assembly, a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer can instruct, in response to the received pilot command, the flight control system to change a first operating condition of the flight control system based on an inherently-coupled relationship between the first flight characteristic and the second flight characteristic. The flight control computer can instruct, in response to the expected change to the second flight characteristic, the flight control system to change a second operating condition of the flight control system.

Abstract: An aircraft control system includes a propeller shaft assembly. Also included is first rotor operatively coupled to the propeller shaft assembly, the first rotor having a first plurality of blades mounted thereto, the first blades disposed at a substantially identical nominal pitch during rotation of the first rotor, the first rotor rotatable in a first direction. Further included is a second rotor operatively coupled to the propeller shaft assembly and rotatable in a second direction, the second rotor having a second plurality of blades mounted thereto, wherein a pitch of the second blades cyclically changes during rotation of the second rotor, the first rotor and the second rotor disposed and rotated proximate a fixed wing of an aircraft about a common axis extending parallel to a longitudinal axis of the aircraft, cyclically changing the pitch of the second plurality of blades generating a moment for controlling the aircraft.

Abstract: A family of Radar energy Absorbing Deformable Low Drag Vortex Generators (RAD-LDVG) is described herein. This family of devices are fabricated in such a way that it can conform to aircraft surface features while reducing radar returns from structural details. Vortex generators (VGs) are typically used to reattach or smooth gross flowfields over aircraft surfaces. By doing so, an airfoil or wing can maintain attached flow at higher angles of attack and/or higher lift coefficients than one without the VGs. These devices are also used to reattach and/or smooth flows that encounter crossflow-induced instabilities and/or adverse pressure gradients on the upper surfaces of wings or near aircraft boattails. Other uses include reduction of buffet, vibration, flutter, cavity resonance or general bluff-body pressure drag reduction. Although conventional rigid VGs do generate vortical aerodynamic structures, two major problems are often experienced: i.) the inability to conform to curved surfaces, ii.

Abstract: Methods and related apparatus embodiments are disclosed that allow novel Conformal Vortex Generator and/or Elastomeric Vortex Generator art to improve energy efficiency and control capabilities at many surface points of a body or object moving at speed in aero/hydrodynamic Newtonian fluids, by reducing; shock energy losses, surface flow turbulence, and/or momentum layer thicknesses.

Abstract: A fastening system having differentiable components includes a first bushing with a first mating feature to be inserted within a first receiver. A first fuse pin with a second mating figure and being configured to shear upon the application of a first predetermined load is configured to be inserted into the first receiver and mate with the first mating feature of the first bushing. The first and second mating features correspond and permit the insertion of the first fuse pin into the first bushing within the first receiver to selectively connect components. The first bushing may prevent the complete insertion of a second fuse pin having a third mating feature into the first receiver. A second bushing having a fourth mating feature may permit the complete insertion of the second fuse pin into the second bushing positioned within a second receiver.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) landing gear assembly that includes adjustable landing gear extension that may be extended or contracted so that the body of the UAV is contained in a horizontal plane when the UAV is landed, even on sloping surfaces. For example, when a UAV is landing, the slope of the surface may be determined and the landing gear extensions adjusted based on the slope so that the body of the UAV remains approximately horizontal when the UAV lands and is supported by the landing gear extensions.

Abstract: A drive system for rotating a wheel of an aircraft landing gear. The drive system has a drive pinion and a motor operable to rotate the drive pinion via a drive path. A rotary damper is provided in the drive path between the motor and the drive pinion. A driven gear is adapted to be attached to the wheel so as to be capable of rotating the wheel. The drive system has a drive configuration in which the drive pinion is capable of meshing with the driven gear to permit the motor to drive the driven gear via the drive path. One of the drive pinion and the driven gear comprises a roller gear having a series of rollers arranged to form a ring, each roller being rotatable about a roller axis, and the other of the drive pinion and the driven gear comprises a sprocket.

Abstract: A helicopter is described that comprises: a rotor; a fuselage; a drive transmission unit operatively connected to the rotor; a support body, which supports the transmission unit; and constraining means interposed between the support body and the fuselage; the constraining means in turn comprise a crosspiece connected in a fixed manner with respect to the support body and having a first lying plane; the crosspiece is formed in part by a metallic material and in part by a visco-elastic material.

Abstract: A rotor assembly for a rotary wing aircraft includes a rotor hub having a central axis, the rotor hub rotatable about the central axis. A plurality of flexible structural members extend radially outwardly from the rotor hub, each flexible structural member substantially U-shaped and having a first arm extending from the hub, a second arm extending from the hub, and an end portion connecting the first arm to the second arm at a radially outboard end of the flexible structural member. A clamp member is positioned between the first arm and the second arm of each structural member and secured thereto to tie deflection of the first arm to deflection of the second arm. A rotor blade is secured to each flexible structural member of the plurality of flexible structural members via the clamp member.

Abstract: A drive system for a tiltrotor aircraft includes a first gearbox rotatably mounted to the airframe and rotatable about a longitudinal axis to operate the tiltrotor aircraft between helicopter and airplane modes. A second gearbox extends generally normal to the longitudinal axis of the first gearbox. A common shaft, rotatable about the longitudinal axis, transfers torque from an output gear of the second gearbox to an input gear of the first gearbox. A support assembly couples the second gearbox to the airframe and includes a fixed joint proximate the longitudinal axis, a first directional reacting joint remote from the longitudinal axis providing a first radial growth degree of freedom to the second gearbox and a second directional reacting joint remote from the longitudinal axis providing a second radial growth degree of freedom to the second gearbox that is not parallel with the first radial growth degree of freedom.

Abstract: A system, apparatus and methods for an airspace plane with shockwave piercing leading edge slots has been described. Which mainly combines concepts of thermodynamic sequencing, heat transfer dynamics, boundary layer separation, spatial adaptivity and Carnot conformance. Wherein the leading-edge slots may be thermally conductive and have converging or diverging double decker structures.

Abstract: Technologies and implementations for using unmanned aerial vehicles in medical applications.

Abstract: This invention relates to a drone, method and systems for displaying messages and/or images by using a group of one or more remotely controlled airborne drones provided with display means and controlled so the messages and/or images are created and are visual by the display means of the group of airborne drones. The display means are controlled such that the messages and/or images are 2D or 3D respectively. The display means may include LED's, OLED's or LCD based on means or DLP and/or laser projection means. The display of messages and/or images can be remotely controlled using a social gateway for airborne visualization, enabling the integration of content from end-user and marketing clients based on the drone's geographic position and social media audience profile.