Abstract: An animal flotation device is provided. The animal flotation device is a non-inflatable, semi-submersible flotation apparatus for a dog to stably sit, lay and move about while partially submerged in a body of water of any depth. The animal flotation device may have a peripheral portion defining an interior portion. The interior portion provides a generally rigid area adapted to become semi-submersed within the body of water when supporting the dog, whereby the peripheral portion provides buoyancy and stability to the semi-submersed interior portion so that the dog may move around and feel safe while floating atop the body of water.

Abstract: Accessory mounting systems for stand up paddle boards are disclosed. In one example, the accessory mounting system includes a mounting plug secured to a stand up paddleboard, a accessory plate secured to the mounting plug, and one or more accessories secured to the accessory plate. In other examples, the accessory plate is provided with an adhesive backing and can be mounted and secured to the stand up paddle board, thereby allowing the accessory mounting system to be used on boards not having mounting plugs and/or at locations where mounting plugs are not present. In yet another example, a mounting track is provided instead of a accessory plate such that one or more accessories, such as fishing rod holder, can be slidably mounted on the stand up paddle board.

Abstract: The present invention is directed to a visual distress signal device that includes a housing having an internal cavity with a first electrical contact and a power source positioned therein in an electrically coupled manner. An electronic assembly is at least partially positioned within the internal cavity of the housing. Such an electronic assembly may include a second electrical contact that is electrically coupled to the power source, a third electrical contact, and a light source. The device may also include a lens member detachably coupled to the housing to close an open top end of the housing in a watertight manner. A float member may be detachably coupled to the housing to provide buoyancy to the device. The electronic assembly may be movable within the internal cavity to electronically couple and decouple the third electrical contact and the first electrical contact to selectively power the light source.

Abstract: A landing watercraft boat hull with push knees and side bumper assemblies that include a vertical rigid frame aligned parallel to the hull's longitudinal axis. The rigid frame's front edge extends in front of the bow of the hull. Attached to the rigid frame's top edge and extending over the rigid frame's front edge is an L-shaped front bumper. In one embodiment there are two assemblies located on opposite sides of a landing door. The rigid frames are sufficient in length so the front edges of the two L-shaped bumpers are disposed in front of the bow enabling the hull to safely push against other hulls or objects and protect the landing door. Attached to the outside surface of each rigid frame is a rigid shell cover that extends rearward from the rigid frame. The cover includes a rear opening in which the distal end of a side bumper attached to the side of the hull is inserted to hold and protect the distal end of the side bumper.

Abstract: A flotation apparatus having a first elongate member, a second elongate member, and a connector, such as an exterior housing, engaging the first and second elongate members and deforming the first elongate member into a curved shape. Ends of the first elongate member are positioned proximate to ends of the second elongate member to define gaps therebetween that permit movement of one or both elongate members relative to the other.

Abstract: An underwater vehicle for transporting extraction fluids, for example natural gas, oil or water, has an overall elongated form and includes one or more containment tubes configured to contain the fluid to be transported and forming a bundle that prevalently extends longitudinally with respect to the underwater vehicle, making the vehicle structurally more robust and intrinsically safe.

Abstract: A water environment robotic system that includes a control station, an underwater robotic vehicle, and a water-surface robotic vehicle. The underwater robotic vehicle is in communication with the water-surface robotic vehicle and the water-surface robotic vehicle is in communication with the control station. Accordingly, the water-surface robotic vehicle can act as a relay between the control station and the underwater robotic vehicle. The water-surface robotic vehicle is further capable of detecting the position of the underwater vehicle and automatically adjusting the position of the underwater vehicle in order to maintain general vertical alignment between the two vehicles.

Abstract: A folding propeller for a boat, e.g., for a sailboat or a multihull yacht, and a method for installing and/or adjusting such a folding propeller, where said folding propeller has a hub for directly or indirectly fastening at a driveshaft connected to a motor, where said folding propeller further has at least two individual blades, where each of said blades has a root arranged to pivot around a pivot pin at said hub to be either in a first, operative position, where the blades are pointing mainly in a radial direction, and in a second, inoperative position, where the blades are pointing mainly in an axial direction, where said hub has one or more cut outs for said blades roots and further has a first set of holes for installing said pivot pins and a second set of holes for installing a locking device for engagement with said pivot pins.

Abstract: A paddle device, where this principle described may be configured to accommodate canoe, kayak, paddle boards or any similar watercraft using a paddle type device. This paddle device comprises a shaft having a first end and a second end with a paddle-like blade having a proximal end and a distal end and coupled to the second end of the shaft. This paddle blade device is equipped with one or more multi-blade propellers that are mounted on the paddle blade. The multi-blade propeller or multi-blade propellers are driven by the pulling motion of the paddler or driven by the action of the natural water current the paddler is navigating. The propeller is designed to swivel so as to keep the propeller blade more in direct alignment with the force of the water driving it. This insures that the propeller is at the most efficient angle to help propel and control the watercraft. The propeller or propellers are protected with a lattice type guard on both sides of the paddle blade.

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 connection system includes a first adhesion segment, on which a first planar bonding region is formed; a second adhesion segment, on which a second planar bonding region is formed, which is shaped so as to be complementary to the first planar bonding region, and a solidifiable, liquid bonding substance. The first planar bonding region and/or the second planar bonding region are each provided with receiving openings. The receiving openings extend like capillaries through each bonding region into the interior of each adhesion segment and, in order to form an integral bond between the first adhesion segment and the second adhesion segment, are designed such that the receiving openings receive the liquid bonding substance due to capillary ascension during application of the liquid bonding substance onto each bonding region.

Abstract: A rotary wing aircraft comprising a fuselage, a cabin volume enclosed by the fuselage, a main rotor arranged above the fuselage, a tail rotor mounted on a tail, the tail being attached to a rear part of the fuselage supporting the tail at its rear end, whereas the tail includes two beam boom elements, one element extending at the port side and the other element extending at the starboard side of the rotary wing aircraft, the front root end of each element being hinged to the corresponding lateral side of the fuselage, and both elements being canted with respect to the longitudinal axis of the rotary wing aircraft so as to be interconnected to each other at the rear portion of the tail.

Abstract: An aircraft wing comprising a load transfer apparatus arranged to transfer transverse shear loads from a first component such as a wing skin to a second, adjacent component such as a wing skin. The apparatus comprises a master interlock, and a plurality of slave interlocks. Each master interlock comprises a master male member received in a master female member to form the master interlock. Each of the plurality of slave interlocks comprises a slave male member received in a corresponding female member to form the slave interlocks. The master male and female members are sufficiently stiff that the master male member and the master female member are fixed, whereas the slave male and/or female members are less stiff than the master male and female members such that the slave male and/or female members are able to tolerate some movement, in the transverse direction.

Abstract: An aircraft structure comprising a wing tip device connected to a wing by a plurality of connectors, wherein each connector comprises a spigot associated with the wing tip device or the wing, and a lug associated with the other of the wing tip device or wing. The lug has a hole for receiving the respective spigot. The spigot of each connector is moveably mounted, relative to said wing tip device or wing, about a central position, such that during movement of the connectors from a dis-engaged configuration to an engaged configuration, each spigot can move away from the central position to align itself with the hole of the respective lug.

Abstract: A propeller blade assembly includes a spar extending along a propeller blade axis and an outer sleeve surrounding the spar portion at a root end of the rotor blade assembly. The spar is adhesively bonded to the outer sleeve at an interface portion. A spar maximum diameter along the interface portion is larger than an outer sleeve minimum diameter along the interface portion. A method of assembling a propeller blade includes installing an outer sleeve over a spar at a root end of the spar, the spar a not fully cured composite component, and urging the spar into compressive conformance with the outer sleeve at an interface portion of the propeller blade assembly. A spar maximum diameter along the interface portion is larger than an outer sleeve minimum diameter along the interface portion. The spar is cured thereby adhesively bonding the spar to the outer sleeve at the interface portion.

Abstract: An apparatus and method for controlling an actuator. A plurality of commands for the actuator are received from a number of primary controllers by a command lane and a monitor lane. The command lane selects a first selected number of commands from the plurality of commands using a selection rule. The monitor lane selects a second selected number of commands from the plurality of commands using the selection rule and generates a check value for the second selected number of commands. The first selected number of commands from the command lane and the check value from the monitor lane are combined to form an actuator control command message comprising the first selected number of commands and the check value. The actuator control command message is sent to an actuator controller for controlling the actuator.

Abstract: Apparatus and methods for robust lift generation through flow separation suppression are disclosed. One example apparatus includes a cowling extending from a surface of a fluid dynamic body to provide an exhaust stream directed over the fluid dynamic body. The example apparatus also includes a fluid ejection slot proximate or on the fluid dynamic body, where the fluid ejection slot is to direct a compressed fluid along a surface of the fluid dynamic body. The example apparatus also includes rotatable vanes having blunt leading edges, where the vanes are proximate the fluid ejection slot to direct the compressed fluid to affect attachment of the exhaust stream to the fluid dynamic body to enhance lift.

Abstract: In one embodiment, a wing includes a low pressure side, a high pressure side opposite the low pressure side, and a drag reducing apparatus coupled to the low pressure using an adhesive. The drag reducing apparatus includes a first side coupled to the low pressure side of the wing, and a second side opposite the first side, the second side comprising a plurality of vortex generators arranged in an array configuration, the array configuration of vortex generators operable to weaken a wingtip vortex generated by the wing by generating one or more vane vortices near an end of the low pressure side of the wing.

Abstract: An aircraft landing gear assembly includes a bi-stable, split line tube biased to assume a tubular condition to serve in place of a lock link or side stay and an actuator configured to radially enlarge the tube at a region for folding.

Abstract: The present disclosure describes composite actuator piston rods and methods for making such rods. Composite actuator piston rods of the present disclosure may include a flared end and an embedded nut positioned within the flared end. A rod end assembly may be secured to the embedded nut. The rod end assembly may include a rod attachment end with a threaded surface configured to engage the embedded nut and a edge configured to compress a portion fo the flared end. The rod end assembly may also include an external nut proximate to the wedge nad configured to exert a force against the wedge.

Abstract: An aircraft landing gear assembly includes a fibre composite leaf spring arranged as a down lock spring to make the lock link.

Abstract: In some embodiments, the steering of an aircraft is enhanced by the use of a steering control system. The steering control system may include a steering request unit, a speed measurement unit, a steering control unit, and a steering control device. The steering control system is operable to generate and transmit to a steering control device, a wheel position request based on a steering request and the speed of the aircraft.

Abstract: A steering device for an aircraft landing gear leg including a main fitting has a steering collar for rotatably mounting on the outside of the main fitting; an actuator having an actuator body; and an actuator arm arranged to move between an extended position and retracted position with respect to the actuator body. The actuator arm is pivoted to the main fitting, and a bracket is pivoted to the main fitting; a second pivot location pivoted to the actuator body; and a third pivot location pivotally connected to one end of a steering arm. The steering arm is pivoted at its other end to the steering collar. Also, an aircraft landing gear with the steering device and aircraft having the landing gear.

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: An aircraft landing gear shock absorber having an inner housing portion slidably coupled within an outer housing portion, and a chamber which defines a sealed fluid volume for containing shock absorber fluid within the shock absorber. The chamber includes a moveable wall portion arranged to move between a first position and a second position, and in the second position the effective volume of the chamber is decreased such that the shock absorber fluid pressure increases, to provide a bump to the shock absorber.

Abstract: A reconfigurable unmanned aircraft system is disclosed. A system and method for configuring a reconfigurable unmanned aircraft and system and method for operation and management of a reconfigurable unmanned aircraft in an airspace are also disclosed. The aircraft is selectively reconfigurable to modify flight characteristics. The aircraft comprises a set of rotors. The position of at least one rotor relative to the base can be modified by at least one of translation of the rotor relative to the boom, pivoting of the boom relative to the base, and translation of the boom relative to the base; so that flight characteristics can be modified by configuration of position of at least one rotor relative to the base.

Abstract: A rotor hub for a reaction drive type helicopter includes a cylindrical sidewall having a top and an open bottom which defines an interior volume. A top plate closes the top of the cylindrical sidewall, and at least two pipe sections extend outwardly from the cylindrical sidewall. Each pipe section extends through the sidewall in communication with the interior volume. A horizontal vane is carried in an inlet of the pipe section and extends horizontally across the inlet. A three dimensional body extends downwardly from a central axis of the top plate into the interior volume.

Abstract: The invention is directed toward a UAV having a plurality of rotors position on axles extending longitudinally from a fuselage. The axles articulate the rotors from a vertical position, where the rotors provide lift, to a horizontal position, where the rotors provide thrust. The UAV is configured such that the voltage provided to each rotor may be varied to adjust rotor speed, and thus thrust, independently, giving the UAV enhanced maneuverability.

Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

Abstract: A vehicle which can travel on land, in water, or through air has a body like that of an automobile with powered wheels for providing propulsion on land. The vehicle also has rotors for providing propulsion in air and wings for providing lift. Storage compartments conceal the rotors during land operation, and in this mode the wings are folded down against the body, over the compartments. The wings and the rotors can be deployed to convert the vehicle to flight mode.

Abstract: Systems, methods, and devices are provided that enable robust operations of a small unmanned aircraft system (sUAS) using a compound wing. The various embodiments may provide a sUAS with vertical takeoff and landing capability, long endurance, and the capability to operate in adverse environmental conditions. In the various embodiments a sUAS may include a fuselage and a compound wing comprising a fixed portion coupled to the fuselage, a wing lifting portion outboard of the fixed portion comprising a rigid cross member and a controllable articulating portion configured to rotate controllable through a range of motion from a horizontal position to a vertical position, and a freely rotating wing portion outboard of the wing lifting portion and configured to rotate freely based on wind forces incident on the freely rotating wing portion.

Abstract: An unmanned aerial vehicle (UAV) that can operate both as a conventional multicopter with no wing attached, or, it can operate as a winged multicopter. The detachable wing design used in the invention provides versatility without compromising performance; the wing attachment receptacles add no weight to the wingless multicopter configuration because they also function as the leg receptacles. In one embodiment, the base multicopter configuration is a quad-copter with four propeller drives. Four tubular receptacles, two forward and two aft, provide attachment points for the vertical struts of a detachable rectangular shaped wing, these vertical struts also function as the legs of the multicopter. The wing is fabricated using lightweight struts and rip stop nylon fabric which can be easily folded into a compact shape using quick release pins. In another embodiment, the wing is fabricated using a foam core.

Abstract: An unmanned aerial vehicle according to the present invention includes a housing mounted on a vehicle and having an inner space, the housing provided with a launching unit, an unmanned aerial vehicle accommodated in the housing and configured to be launched from the housing when a driving state of the vehicle meets a preset condition, wing units mounted to the unmanned aerial vehicle and configured to allow the flight of the unmanned aerial vehicle in response to the launch from the housing, an output unit disposed on the unmanned aerial vehicle, and a controller configured to control the wing units to move the unmanned aerial vehicle to a position set based on information related to the driving state when the unmanned aerial vehicle is launched, and control the output unit to output warning information related to the driving state.

Abstract: An aircraft comprises a weapons bay, the weapons bay comprising a cavity having an opening through which stores may be deployed, and a door assembly for exposing/closing the opening of the cavity. A first store is held in the cavity via a launcher and a first structure is disposed inside the cavity, for controlling the aero-acoustic environment. The first structure for controlling the aero-acoustic environment is removably mounted in the weapons bay, such that if the first store is exchanged for a second, different, store, the structure for controlling the aero-acoustic environment may be unmounted from the weapons bay and removed, to be exchanged for a second, different, structure for controlling the aero-acoustic environment.

Abstract: Reconfigurable payload systems (RPS) and methods of configuring and using the same are disclosed that may be employed to enable external aircraft payloads to be rapidly interchanged or swapped out together with associated internal equipment within a given aircraft so as to modify or change payload capability of the aircraft, e.g., to meet a particular mission and/or to enable use of future payload types as they are developed. The RPS and associated methods may be implemented to allow multiple different payload systems to be swapped in and out on a given aircraft as required based on needs for a given mission.

Abstract: Embodiments described herein relate to quick release toilet concepts, which can be useful particularly on-board aircraft and other passenger transport vehicles. Further embodiments relate to improved shroud components for toilets that help reduce splash. Further embodiments also relate to flushing systems for use with vacuum toilets.

Abstract: A combination lavatory and galley arrangement for aircraft includes a lavatory portion having adjacent inboard and outboard lavatories, and a galley portion, and can be located aft of aft aircraft aft doors, and can at least partially rearwardly extend into the aircraft's aft pressure dome. The inboard and outboard lavatories can be separated by a movable wall or partition to provide access for persons with restricted mobility, and can be provided in a modular housing to facilitate retrofit assembly within an aircraft. The movable wall can be an articulating movable lavatory partition movable between a first, linearly extended configuration and a second, folded configuration in a stowed position to provide entry for persons with restricted mobility.

Abstract: Modular constructs are disclosed wherein a plurality of structural members, most often parallel to one another, form spaced-apart layers. Clamping force, applied in some embodiments approximately perpendicularly to a face of each structural member through use of one or more tension assembly comprising a cable, rope, wire, rod, or the like, in association with one or more tubular spacer, is used to draw the structural members into alignment and to provide structural integrity of the modular construct. The subject matter of the present disclosure further relates to processes for creating such layered modular constructs. The subject matter of the present disclosure may find particular application within modular structures, such as, but not limited to, those for aircraft, boats, and other means of transportation, buildings, storage spaces, furniture and cabinetry, modular support systems for electronic equipment, support structures, interfaces, prosthetics, rack systems, modular work partitions, and the like.

Abstract: Two seats (16) are arranged facing in opposing directions, wherein each seat comprises a seat back (40), a headrest (48), and a seat pan (42). Each seat is configured to convert between a seat position and a bed position. A partition (18) is positioned between the two seats.

Abstract: An aircraft passenger seat having a seat bottom movable between a stationary position for taxi, take-off and landing and a movable position during flight in which at least one of a leading edge and a trailing edge of the seat bottom deflects downward in response to a downward load applied thereto.

Abstract: Described are passenger seats with a seat pan (12) releasably coupled to a seat frame (14) via at least one coupling device (20), which includes a ramp (22) mounted on a lower surface (36) of the seat pan (12) and a latch (42) pivotally coupled to an open end of the ramp (22). The latch (42) includes a flap configured to substantially cover the open end of the ramp (22) when the latch (42) is in a closed position, and a handle (48) that is accessible from an upper surface of the seat pan (12) via an aperture (50) in the seat pan (12). The coupling device also includes a spring (44) configured to position the latch (42) in the closed position until a force is applied to the handle (48) to rotate the latch (42) to an open position.

Abstract: A three dimensional lattice panel structure having a multitude of mutually offset holes formed in a respective top and bottom of the panel and intersecting to form voids with interspersed support posts interconnecting the top and bottom of the panel in areas not encompassed by the mutually offset holes.

Abstract: A seat headrest is provided that includes a mounting plate for attachment to a seat back of the seat. First and second side wings are mounted on opposite ends of the mounting plate. The side wings are mounted for pivotal movement between a retracted position against the mounting plate and a deployed position extending outwardly away from the mounting plate, and for sliding movement between the retracted position against the mounting plate and a further deployed position extending outwardly away from the mounting plate.

Abstract: An armrest assembly comprising a base structure and an upper structure that has an upper surface providing an armrest. The upper structure is movable with respect to the base structure between an upper position and a lower position under the control of a lockable actuator that is operable to lock the upper structure with respect to the base structure in any one of a plurality of adoptable positions. A second locking device is operable to lock the upper structure with respect to the base structure in at least one of the adoptable positions, the locking device including locking elements that inter-engage mechanically when the second locking device locks the upper structure with respect to said base structure.

Abstract: An air cycle machine comprises rotating components that include a fan, a compressor, and a first turbine. The air cycle machine also includes a cooling airflow path that receives cooling air from a cooling air source, directs the cooling air to an air-cooled bearing for at least one of the rotating components, and discharges the cooling air. The airflow path is isolated from an inlet of the compressor by a seal member, and the airflow path is configured to maintain pressure at the seal member above a pressure at the compressor inlet.

Abstract: An aircraft comprising a heat exchanging pack comprising an energy recovering module with a hot and a cold side, the hot side thermally contacting the cold side, providing a heat exchange. The heat exchanging pack also comprises a secondary heat exchanger and a compressor coupled with a turbine. The hot side module inlet fluidly communicates with the bleed air duct, the cold side module inlet fluidly communicates with the ram air duct, the hot side module outlet fluidly communicates with the compressor inlet, the compressor outlet fluidly communicates with the hot side secondary inlet, the hot side secondary outlet fluidly communicates with the turbine inlet, and the cold side secondary inlet fluidly communicates with the ram air duct. The energy recovering module comprises a conversion apparatus, configured to generate energy out from the heat exchange taking place in the energy recovering module between the hot and cold sides.

Abstract: Air conditioning system for the pressurised cabin of an aircraft, said system (1) being characterised in that it comprises an air withdrawal module (3) configured for withdrawing ambient air from outside the aircraft, an air compression module (5) configured for compressing the withdrawn air flow (F1) and an air cooling module (10) comprising means (15) for storing at least one coolant configured for cooling the compressed air flow (F2, F3).

Abstract: The present invention provides a windshield device including: a windshield; a heater that is provided in the windshield and configured to generate heat by energization; a temperature sensor that is provided in the windshield and configured to detect a temperature; and a control unit that performs power control on the heater. The control unit is configured to supply an input power to the heater, the input power being acquired by applying a detected temperature detected by the temperature sensor to a function that is determined in accordance with a dew-point temperature of an inside of a compartment separated from an outside of the compartment by the windshield.

Abstract: The present disclosure is related to an autonomous airbag unit (AAU) for an unmanned aerial vehicle (UAV). The AAU includes a first sensor configured to determine a speed of the UAV, a second sensor configured to determine a relative speed of the UAV in relation to an object with which the UAV is likely to collide, an airbag cushion, an inflator connected to the airbag cushion, and an airbag control unit, connected to the first and second sensors and inflator. The airbag control unit is configured to estimate a momentum of the UAV based on a speed of the UAV, determine if the momentum of the UAV exceeds a threshold momentum value, determine if the relative speed of the UAV in relation to the object exceeds a threshold relative speed, and enable the inflator to inflate the airbag cushion when the momentum and the relative speed exceeds respective threshold limits.

Abstract: The present invention provides a water inflow prevention device for aircraft, working when landing in water, the device including: a blocking body for blocking a flow channel from an outside of the aircraft when landing in water, the flow channel allowing the inside and outside of the aircraft to communicate with each other, and a valve element of a pressure adjusting valve being positioned in the flow channel; and a connection part that is deformed when landing in water, wherein the blocking body is supported by a member constituting an end of the flow channel on a side outside the aircraft through the connection part, and the connection part is deformed in a direction so as to block the flow channel by the blocking body, with use of force of water acting on the blocking body when landing in water.