Abstract: A modular transporter comprises a universal chassis that can be linked with a variety of user modules. The universal chassis comprises a base that includes a quick connector and complex geometric surfaces on its sidewalls that function to secure a user module thereto. The quick connector allows for quick assembly/disassembly of a user module to and from the base of universal chassis. A plurality of suspension arms may be removeably connectable to the base such that modular transporter may be configured in a number of transport configurations. An ergonomic handle assembly may be coupled with the base for pushing, pulling, towing, etc. When disassembled, the modular transporter can be folded into a storage and/or quick fold mode and stored in a modular storage system. The modular storage system can be mounted to a trailer hitch by a linking mechanism for further transport.

Abstract: A bicycle disc brake caliper is provided that may include a caliper body with a brake disc slot configured to at least partially accommodate a disc brake rotor removably arranged therein, first and second brake pads movably arranged in the brake disc slot relative to one another to contact the disc brake rotor arranged at least partially in a space between the first and second brake pads, and a spacer movably attached to the caliper body. The spacer may be configured to be positioned in a first position outside the space when the disc brake rotor is arranged in the brake disc slot, and the spacer may be configured to move from the first position to a second position in which the spacer is positioned in the space when the disc brake rotor is removed from the brake disc slot.

Abstract: Powertrain for a pedal vehicle Powertrain for a pedal vehicle comprising a first (20) and a second (4) motor as well as an planetary gearing (3) having a planet carrier (14, 114), a ring gear (12, 112) and a sun gear (13), which first motor (20) is connected to the planetary gearing (3), which powertrain also comprises a crank axle (11) to which the ring gear (12, 112) is connected to create a first input to the planetary gearing (3), the second motor (4) is geared to the crank axle (11), a control unit (6) being de signed to regulate the first motor (20) according to an angular position setpoint, and the second motor (4) according to a current or torque setpoint.

Abstract: This disclosure generally relates to an automatic bicycle, particularly to a hydraulic automatic transmission bicycle which can automatically and adaptively change gear ratios. More particularly, this disclosure relates to those hydraulic automatic transmission bicycles which use fluid pressure to change such gear ratios, and which include various hydraulic automatic transmissions which may be provided in various configurations and may operate in various methods and sequences to provide automatic and infinitely variable gear ratios.

Abstract: A catamaran lifting apparatus is disclosed for lifting objects in a marine environment. The apparatus includes first and second vessels that are spaced apart during use. A first frame spans between the vessels. A second frame spans between the vessels. The frames are spaced apart and connected to the vessels in a configuration that spaces the vessels apart. The first frame connects to the first vessel with a universal joint and to the second vessel with a hinged connection. The second frame connects to the second vessel with a universal joint and to the first vessel with a hinged or pinned connection. Each of the frames extends upwardly in an inverted u-shape, providing a space under the frame and in between the barges that enables a marine vessel to be positioned in between the barges and under the frames.

Abstract: Disclosed is a portable platform with a plurality of panels configured to have a folded state and an extended state, wherein the platform is buoyant in water. The platform is configured to provide a substantially horizontal surface above a water surface when in the extended state and placed in a body of water. A first one of the plurality of panels is a support panel that may include a heat resistant support plate on which a barbecue or stove may be placed and/or secured. A second one of the plurality of panels has an aperture configured such that the barbecue fits through the aperture when the platform is in the folded state. A third one of the plurality of panels that is a cover panel that enables the platform to enclose the barbecue when in the folded state. The cover panel may have a heat resistant protective plate and the protective plate on the cover panel may have a recess to accommodate the barbecue when the platform is in the folded state.

Abstract: Disclosed is a tower system for a transportation device, the tower system including a tower including a first tower leg, a second tower leg, and a center tower section connecting said first tower leg and said second tower leg; and a frame configurable with a cover, said frame including at least one mount for affixing said frame to said center tower section at at least one affixing point on said tower section, wherein said at least one affixing point is disposed at an interior of said. area of said center tower section, away from said first tower leg and said second tower leg.

Abstract: An apparatus for towing a personal watercraft, including a towing member and a stabilizing member. The towing member is configured to attach a rear portion of the towing watercraft to a front portion of the personal watercraft. The stabilizing member comprises an elongated rigid body configured to attach to the rear portion of the towing watercraft and to extend to a stabilization point above a rear portion of the personal watercraft, and a flexible line member extending from the stabilization point of the elongated rigid body for attachment to the rear portion of the personal watercraft. The flexible line member is configured to limit lateral movement of the rear portion of the personal watercraft relative to the towing watercraft.

Abstract: An object that can be towed in a fluid by a cable along a substantially horizontal transport axis comprises a body suspended under gravity from the cable by a fixing arm, and an exterior hydrodynamic surface that is symmetric with respect to a vertical plane containing the transport axis, so as to limit the lateral lift of the body, and an opening passing through the body along a vertical axis and configured to equalize the pressures of fluid flowing along the exterior surface, making it possible to limit the hydrodynamic forces that may be generated perpendicular to the transport axis giving rise to a force in rotation about the transport axis opposing the effect of gravity.

Abstract: The present disclosure describes an attachment apparatus for a water sport article, the attachment apparatus configured to hold goods having a base plate having an attachment portion for attachment to the water sport article, a shaft coupled to the base plate on a first end, and removable from the base plate and being adjustable in height, a holder coupled to the shaft, the holder being detachable from the shaft. A method for attaching a holder to water sports article is also provided.

Abstract: A water habitat platform is created from converted trash and rubbish found within the oceans. A process separates the trash from water to identify the raw materials, which are then converted into building blocks. The blocks are used to create platforms or islands that sustain themselves using power generated from tidal forces. The islands are connected to each other and moveable.

Abstract: A personal life raft includes a rigid compartment, a first flexible arm member in sealed engagement with a first port on a first side of the rigid compartment, a second flexible arm member in sealed engagement with a second port on a second side of the rigid compartment. Each of the first flexible arm member and the second flexible arm member are impervious to water or waterproof such that water does not pass therethrough. The rigid compartment has a body chamber therein having a volume to encompass at least an upper torso of a user of the personal life raft. The rigid compartment displaces sufficient water so that the personal life raft is buoyant while in use by the user.

Abstract: A sea-surface vessel configured to operate in an autonomous mode and to implement autonomous operation of one or more undersea autonomous vehicles is described herein.

Abstract: This disclosure provides improved nautical craft that can travel and navigate on their own. A hybrid vessel is described that converts wave motion to locomotive thrust by mechanical means, and also converts wave motion to electrical power for storage in a battery. The electrical power can then be tapped to provide locomotive power during periods where wave motion is inadequate and during deployment. The electrical power can also be tapped to even out the undulating thrust that is created when locomotion of the vessel is powered by wave motion alone.

Abstract: A vessel power supply system for a vessel including a propulsion device that includes an engine and a generator driven by the engine to generate electricity, includes a first battery that supplies power to the propulsion device, a second battery that supplies power to accessories of the vessel, a first open circuit voltage sensor that detects an open circuit voltage of the first battery, a second open circuit voltage sensor that detects an open circuit voltage of the second battery, and a switch that is turned on/off to open and close a current path between the first battery and the second battery.

Abstract: A Shipboard Auditory Sensor (SAS) for detection and classification of acoustic signaling at sea is capable of detecting whistles blasts from other vessels in accordance with Rules 34 and 35 of COLREGS to support autonomous operations in a maritime environment.

Abstract: A decompression device has at least one decompression member which is arranged on a supporting structure and which, in the event of differential pressure of a predetermined level, opens an opening in the supporting structure that acts as a connection between two volumes, wherein the decompression member can move between a retention position, in which the decompression member closes the opening, and a released position, in which the decompression member opens the opening, and has a locking arrangement which, when in use, fixes the decompression member in the retention position. The locking arrangement is provided with at least one locking element, which is arranged on the supporting structure, and the decompression member is kept in the retention position indirectly by the locking element interacting with an air conduction part.

Abstract: A tension-only member for a truss structure and a method of operating a vehicle with tension-only members is provided. Tension-only members readily deform when a compressive load is applied. The tension-only members may be a leaf spring, a strap, a cable, or a rope between two connector ends. The tension-only members are placed diagonally in a truss such that the tension-only members support a load applied in one direction but deflect when a load is applied in an opposite direction. A truss structure with such tension-only members can be flexible to enable a vehicle frame to which it is attached to flex.

Abstract: Systems and methods are provided for securing aircraft sidewall. One embodiment comprises a hanger for supporting sections of sidewall for an aircraft. The hanger includes an elongated vertical member that attaches to a frame of the aircraft, and sets of keyholes that are each arranged in a vertical pattern along the member and that are each configured to support a corresponding section of sidewall of the aircraft. Each keyhole includes a receptacle dimensioned to receive a fitting from a section of sidewall, and a slot dimensioned to slidably accept the fitting via the receptacle to secure the fitting in place. The slot size of keyholes in each set varies from one end of the vertical pattern to another end of the vertical pattern.

Abstract: A heavy-lift UAV frame includes a central frame portion having a symmetrical shape and forming a pocket area for receiving an avionics package. Top and bottom plates are secured to the central frame portion and include four corner members that extend diagonally outward therefrom. A plurality of boom arms are pivotally connected to the corner members and transition between an extended position for flight and a retracted position for storage and transport. Each boom arm includes a complementary dimension to one side of the central frame portion and is arranged parallel thereto when in the retracted position.

Abstract: Pressure bulkhead apparatus is disclosed. An example bulkhead apparatus includes a frame and a plurality of beams radially spaced relative to a longitudinal axis of the frame. A beam from the plurality of beams has a first end and a second end. A beam end assembly couples the second end of the beam and a stringer of a fuselage. The beam end assembly enables the second end of the beam to move relative to at least one of the frame or the stringer.

Abstract: A method and apparatus are presented. The apparatus comprises a first unitary structure, a second unitary structure, and a number of joints between the first unitary structure and the second unitary structure. The first unitary structure has a plurality of T-shaped cross-sections. The second unitary structure has a plurality of T-shaped cross-sections.

Abstract: A coated transparency includes: a transparency; a base layer on the transparency, the base layer comprising at least one selected from an organic compound, an organosilicon compound, and a polysiloxane compound; a metal layer physically contacting the base layer; and a metal oxide layer on the metal layer, the metal oxide layer comprising aluminum doped zinc oxide (AZO).

Abstract: A composite insulation is included between the skin of an aircraft and interior trim panels. The composite insulation includes multiple layers of micro-perforate material interspersed with layers of semi-rigid material. For a given thickness, the composite insulation provides superior transmission loss over a wide range of frequencies, including low frequencies, compared to conventional homogeneous insulation having the same thickness. Thus, the composite insulation reduces broadband noise within the cabin of an aircraft more effectively compared to conventional insulation.

Abstract: Methods and apparatuses may include a stiffened beam assembly including a structural beam portion having a web and upper and lower flanges, and at least one continuous stiffening member extending back and forth between the upper and lower flanges on one side of the web, forming one or more trusses or other reinforcing structures. The beam portion and/or the stiffening member(s) may comprise formed sheet metal. The stiffening member(s) may be mechanically attached to the beam portion.

Abstract: An apparatus for selectively increasing a wing area of an aircraft having a fuselage with an interior space includes an inflatable wing moveable between a stowed condition located in the interior space and a deployed condition located outside the interior space. A plurality of reels is secured to the aircraft. A plurality of suspension lines connects the wing to the reels. At least one reel is operable to unwind a corresponding suspension line to allow the wing to inflate to the deployed condition exclusively by ram air generated by movement of the aircraft. A method of use for a deployable wing is also provided.

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

Abstract: An unmanned aerial vehicle with deployable components (UAVDC) is disclosed. The UAVDC may comprise a fuselage, at least one wing, and at least one control surface. In some embodiments, the UAVDC may further comprise a propulsion means and/or a modular payload. The UAVDC may be configured in a plurality of arrangements. For example, in a compact arrangement, the UAVDC may comprise the at least one wing stowed against the fuselage and the at least one control surface stowed against the fuselage. In a deployed arrangement, the UAVDC may comprise the at least one wing deployed from the fuselage and the least one control surface deployed from the fuselage. In an expanded arrangement, the UAVDC may comprise the at least one wing telescoped to increase a wingspan of the deployed arrangement.

Abstract: A high-lift device comprising an airfoil shaped body having a leading edge and a trailing edge and extending in a spanwise direction configured mainly to generate aerodynamic force; a profile structure arranged to be mounted inside of the airfoil shaped body and extending in spanwise direction of the airfoil shaped body that is configured to provide most of the mechanical strength and stiffness; wherein the airfoil shaped body is provided with an opening extending in spanwise direction at one side through which the profile structure can be fastened and remains accessible inside of the airfoil shaped body.

Abstract: A high-lift device includes a flap body which is provided at a rear portion of a main wing which generates a lift for the air vehicle such that the flap body is deployed with respect to the main wing and stowed in the main wing and extends along a wingspan direction of the main wing; and a gap increasing section provided at an end portion of the flap body in an extending direction of the flap body, to increase a gap between the rear portion of the main wing and a front portion of the flap body in a state in which the flap body is deployed.

Abstract: A diverter duct for a propeller includes a second duct element having a semi-annular wedge shape, which is pivotably coupled to the first duct element, a first drive structure configured to drive a pivoting of the second duct element relative to the first duct element and a second drive structure configured to drive a rotation of the first and second duct elements about an axis of rotation of the propeller.

Abstract: A flight control system includes a flight control computer operable in a flight state and a ground state. A high demand trim relief logic is operable by the flight control computer in the ground state. The high demand trim relief logic is configured to automatically modify the neutral position of a rotor when a command input to the flight control computer to control the rotor is near an allowable limit.

Abstract: An assistance method for assisting flying of an aircraft with restriction of possibilities of adjusting the flying parameters depending on the context, and corresponding device are provided. The assistance method for assisting flying of an aircraft includes the steps of: configuring at least one flying mode, the configuration comprising selecting a flying mode selected from among an available flying mode and entering at least one flying setpoint associated with the selected flying mode, presenting the or each configured flying mode, engaging at least one configured flying mode, and flying of the aircraft by an automatic pilot system of the aircraft based on the flying setpoint of the or each engaged flying mode. The method also includes a step for collecting at least one avionics parameter representative of a flying context, and a step for restricting configuration possibilities of the flying modes based on the or each collected avionics parameter.

Abstract: A method for controlling an unmanned aerial vehicle (UAV) is provided. The UAV comprises at least one rotor. The method includes receiving a take-off signal; initiating the at least one rotor to operate with a first preset rotation acceleration in response to the take-off signal; detecting a take-off status information of the UAV, the take-off status information at least comprising a current height of the UAV; determining whether the detected current height of the UAV is equal to or greater than a threshold; and sending a hover signal to the at least one rotor to enable the UAV to hover in the current height in response to the determination that the detected current height of the UAV is equal to or greater than the threshold.

Abstract: A propulsion system for an aircraft includes an electric propulsion engine configured to be mounted to the aircraft at an aft end of the aircraft. The electric propulsion engine includes a fan rotatable about a central axis of the electric propulsion engine. The fan includes a fan shaft mechanically coupled to a power gearbox. The electric propulsion engine also includes an electric motor having a driveshaft, with the electric motor coupled to the power gearbox through the drive shaft. The electric motor rotates the fan through the power gearbox. The driveshaft includes a flexible element for accommodating a misalignment of the electric motor and the power gearbox.

Abstract: Systems, equipment, and methods to deposit energy to modify and control air flow, lift, and drag, in relation to air vehicles, and methods for seeding flow instabilities at the leading edges of control surfaces, primarily through shockwave generation through deposition of laser energy at a distance.

Abstract: An aircraft landing gear assembly including structural members coupled via a coupling including a bearing. The bearing has a body defining a first bearing surface arranged to contact a first counter-face of the coupling. The first bearing surface is defined by a first tubular layer of fibre reinforced polymer of a first type having an axis and containing synthetic fibres of a first type wound around and along the axis of the bearing. The bearing body further has a second tubular layer of fibre reinforced polymer of a second type containing synthetic fibres of a second type wound around and along the axis of the bearing.

Abstract: Systems and methods for a heat-insulated wheel are disclosed herein. A wheel may comprise a wheel body comprising an outer diameter surface, an inner rim on an inboard side of the wheel body, an outer rim on an outboard side of the wheel body opposite the inner rim, and a heat insulator coupled to the outer diameter surface between the inner rim and the outer rim.

Abstract: An aerial vehicle, configured to transport cargo, and including a propulsion system and a foldable cage is described. The foldable cage is substantially linear while in a folded configuration, and substantially circular while in a deployed configuration. Moreover, the foldable cage includes a rods that form isosceles triangles. The rods are coupled together by flexible joints.

Abstract: Some examples of a cable cutting system include a first cutting apparatus that includes a recess to receive a cable. The system includes a second cutting apparatus separate from and attached to the first cutting apparatus. The second cutting apparatus includes multiple cutting surfaces arranged to cut the cable received at the recess.

Abstract: A main rotor blade assembly for a rotary wing aircraft is provided including a main rotor blade root region, a main rotor blade inboard region arranged outboard of said main rotor blade root region, a main rotor blade main region arranged outboard of said main rotor blade inboard region, and a main rotor blade tip region arranged outboard of said main rotor blade main region. At least one of chord, twist, sweep, airfoil shape, and thickness/chord of the main rotor blade assembly has been optimized to achieve balanced high speed forward flight and hover relative to both efficiency and high thrust capability.

Abstract: A vehicle includes a propulsion system using one or more impellers as opposed to propellers. The impellers impart circumferential and radial velocity components to the working fluid, which may be air or water. The air is deflected by counter-vortex chambers in a shroud to convert the circumferential and radial velocity to an axial velocity aligned with the axis of rotation of the impeller.

Abstract: An apparatus comprising a soft in plane rotor yoke comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material having a plurality of first fibers oriented in a first direction, and a plurality of second layers formed of a second composite fabric material having a plurality of second fibers oriented in a second direction. Included is an apparatus comprising a soft in plane rotor comprising two longitudinal side portions connected together via two outboard portions, wherein the outboard portions comprise a plurality of first layers formed of a first composite fabric material, and a plurality of second layers formed of a second composite fabric material, wherein the soft in plane rotor yoke does not comprise any narrow steered slit tape or filament windings.

Abstract: An aircraft is provided including an airframe, an extending tail, and a counter rotating, coaxial main rotor assembly including an upper rotor assembly and a lower rotor assembly. A translational thrust system positioned at the extending tail, the translational thrust system providing translational thrust to the airframe. A horizontal stabilizer with a left elevator and right elevator positioned at the extending tail. A flight control computer to independently control one or more of the main rotor assembly and the elevator through a fly-by-wire control system. The flight control computer is configured to mix a collective pitch of the main rotor assembly and a deflection of the elevator.

Abstract: A flapping wing driving apparatus includes at least one crank gear capstan rotatably coupled to a crank gear, the at least one crank gear capstan disposed radially offset from a center of rotation of the crank gear; a first wing capstan coupled to a first wing, the first wing capstan having a first variable-radius drive pulley portion; and a first drive linking member configured to drive the first wing capstan, the first drive linking member windably coupled between the first variable-radius drive pulley portion and one of the at least one crank gear capstan; wherein the first wing capstan is configured to non-constantly, angularly rotate responsive to a constant angular rotation of the crank gear.

Abstract: A system is provided for maneuvering a payload in an air space constrained by one or more obstacles, and may include first and second aerial vehicles coupled by a tether to a ground station. Sensor systems and processors in the ground station and aerial vehicles may track obstacles and the tether's and the vehicles' positions and attitude to maneuver the payload and the tether to carry out a mission. The sensor system may include airborne cameras providing data for a scene reconstruction process and simultaneous mapping of obstacles and localization of aerial vehicles relative to the obstacles. The aerial vehicles may include a frame formed substantially of a composite material for preventing contact of the rotors with the tether segments.

Abstract: A method and an apparatus for controlling an unmanned aerial vehicle (UAV) are provided. The UAV comprises at least one rotor. The method includes: receiving a take-off preparatory signal instructing the UAV to enter into a take-off preparatory state; controlling the at least one rotor of the UAV to rotate at a preset rotation speed in response to the take-off preparatory signal, wherein the preset rotation speed is smaller than a rotation speed that enables the UAV to hover in the air; and controlling the UAV to enter into a hovering mode under a predetermined condition, wherein the UAV is controlled to hover at a predetermined height in the hovering mode.

Abstract: A method of delivering, over the air, shelled portions of fluids or granular substances containing effective ingredients, to a target, includes the following stages: selecting a type and a size of the shelled portions containing the required effective ingredients, based on mission parameters and physical data of a scene containing the target; conveying the shelled portions to a delivery point, based on the mission parameters and the physical data; and ballistically delivering the shelled portions towards the target, wherein the shelled portions comprise fluids or granular substances covered by shells that provide the shelled portions a ballistic coefficient that is significantly higher than a ballistic coefficient of similar portions without the shells.

Abstract: Systems and methods for operating a hoist and hook assembly may determine a position of a target using a position sensor. A hook assembly may be positioned in response to the position of the target as detected by the position sensor. Positioning the hook assembly may include articulating a boom coupled to a hoist, using one or more local thrust sources on the hook assembly, and/or moving an airframe relative to the position of the target.