Abstract: Embodiments are disclosed of a standup paddle (SUP) board comprising a substantially rectangular shape in outline and having a length dimension that is a whole number multiple of its width dimension. A plurality of link members are disposed at spaced-apart locations along the periphery of the board's deck. Each link member can function, in a first configuration, as a handle for the board; and, in a second configuration, as a linkup for connecting the board in abutting relation to one or more other adjacently located, similarly configured standup paddle boards. With a plurality of such boards connected proximate one another in a desired configuration via such links, an extended upper surface is provided that can serve as a substantially stable platform upon which one or more persons can engage in desired activities.

Abstract: Disclosed is a surfboard foothold with at least one digit that is removably provided to a receiver with a digited footprint in a surface of a surfboard.

Abstract: An entertainment barge includes at least two pontoons, a first deck having a front, rear, right side and left side, is attached to both pontoons. A second deck is disposed above and substantially parallel to the first deck. At least two retractable spuds are attached to the deck and are adapted to be lowered into the water to secure the barge in a fixed position.

Abstract: A ship body control device is provided, which includes a sensor, a propelling force controller, and an autopilot controller. The sensor measures a speed of a ship. The propelling force controller controls a propelling force of the ship. The autopilot controller outputs an instruction to reduce the propelling force to the propelling force controller, when a condition of canceling an automatic cruise in which the speed of the ship matches with an automatic ship speed setting is satisfied.

Abstract: An inflatable flotation device having a reaction chamber with reactants that generate gas when mixed, said reactants being separated by a barrier assembly; an activating mechanism adapted to remove or puncture the barrier assembly such that said reactants mix; and an inflatable compartment fluidly connected to the reaction chamber by means of a pressure sensitive passageway, adapted to open only when the pressure of the gas in said reaction chamber exceeds a predetermined threshold. This ensures that most of the reactants are used up to generate gas before the gas enters the inflatable chamber, thus preventing scattering of the reactants. Some implementations have a reaction chamber without a barrier assembly, comprising reactants that generate gas when mixed with water and an activating mechanism adapted to expose the reactants to water. A variety of manual or automatic mechanisms may be employed to activate the reaction and inflate the device.

Abstract: An oar that uses the resistance of water to turn a paddle back and forth as it rotates along a shaft thus creating propulsion for any watercraft.

Abstract: A control system for jet-powered boats includes a water jet propulsion group; an ejection nozzle of the water jet oriented to direct the water jet at least in a longitudinal direction; a jet deflector changing flow direction of at least part of the water relative to the longitudinal axis of the boat, the deflector being controllable to progressively adjust the part of the diverted water jet and set a neutral thrust condition, in which the boat is stationary, thrusting forward with variable speed and thrusting backward with a predetermined or variable speed; a control member of the deflector position; a setting member of the deflector that adjusts the deflector to achieve a neutral thrust condition, the deflector being adapted for a predetermined and pre-set neutral thrust position; and a control member of the deflector in the preset position of neutral thrust, canceling any subsequent customization settings.

Abstract: A ship body control device is provided, which includes a control lever having a neutral position, and processing circuitry. When the control lever is moved during an automatic cruise, the processing circuitry executes a deceleration control from a speed of a ship body during the automatic cruise, and when the position of the control lever is in agreement with a position for changing to a manual cruise, the processing circuitry changes the automatic cruise to the manual cruise at a rotating speed of an engine according to the position for changing to the manual cruise.

Abstract: A method and apparatus for facilitating the attachment of an internal module in an internal space of an aircraft part is disclosed. The attachment device includes at least one attachment member comprising an attachment shank, a chamber for introducing the attachment member, the chamber including a first orifice through which the attachment shank passes in the installed configuration of the internal module, and a second orifice which serves for the introduction of the attachment member into the chamber from the outside.

Abstract: A separating element (10) for a platform cabin comprises at least one leaf (20), mounted movably between a closed position and an open position, the leaf (20) being subjected to a return force toward its open position, and, for the or each leaf (20), a return member (36) for returning the leaf (20) toward its closed position, said return member (36) comprising a first end (60) articulated at an articulation point (64) movable jointly with the leaf (20).

Abstract: A dust cover for an aerospace window that comprises dust cover having an exterior substrate and an interior substrate in a spaced apart relationship with a substantially transparent coupling agent therebetween. The dust cover is disposed in a spaced apart relationship from an electro-optic element, defining a gap therebetween. The gap 30 mm or less, 25 mm, 20 mm, 15 mm, 10 mm, 8 mm, 7 mm, 6 mm, 5 mm, 4 mm, 3.5 mm, and/or 3 mm. The exterior substrate, the coupling agent, and the interior substrate are comprised of a combination of materials, such that the combination is substantially transparent and operable to resist breaking and maintain sufficient rigidity to prevent the electro-optic from breaking, when a force of 680 N is applied to an interior surface of the interior substrate in the direction of the electro-optic element.

Abstract: There is provided an air grille panel assembly for a vehicle. The assembly includes an air grille panel having air grille openings, a top end, and a bottom end. The top end is configured for coupling to a sidewall panel in a cabin of the vehicle. The bottom end is configured for coupling to a raceway assembly on a floor in the cabin. The assembly further includes a frame member disposed around a perimeter of each of the air grille openings, to define each of the air grille openings, an air grille coupled to the frame member and covering each of the air grille openings, and a cover member releasably attached to the air grille. The assembly is configured for coupling to the sidewall panel, via a float attachment, that allows for a vertical adjustment, to accommodate different installed positions of the assembly in the cabin of the vehicle.

Abstract: A wing-to-body fairing on an aircraft having a fuselage, wing, and a wing root fairing. The wing-to-body fairing includes forward and trailing edges. The forward edge is configured for positioning adjacent a first predetermined location of an aft portion of the wing root fairing. The trailing edge is configured for positioning adjacent a second predetermined location of the aft portion of the fuselage. A convex-shaped forward portion of the fairing is configured to conform to the aft portion of the wing root fairing at the first predetermined location. A concave-shaped aft portion of the fairing is configured to conform to the aft portion of the fuselage at the second predetermined location. An exterior surface of the wing-to-body fairing is gradient optimized to minimize curvature, where the fairing trailing edge is configured with matching angles and contours as the aft portion of the fuselage at the second location.

Abstract: A composite structural member including at least one first flange element made from a first composite material, and at least one first web element made from a second composite material. The at least one first web element is connected to at least one first flange element in a non-coplanar manner along a corresponding mutual first edge via a first corner element made from a third composite material, the mutual first edge extending along a first direction. The third composite material includes a corresponding first plurality of third composite material first fibers and a corresponding second plurality of third composite material second fibers embedded in a corresponding third composite material matrix in a non-parallel orientation with respect to the third composite material first fibers, wherein the third composite material first fibers are nominally orthogonal to the mutual first edge or to the first direction.

Abstract: An articulating flap support housing includes a flap connected to a wing with the flap having a range of deployed positions. An aft fairing is connected to the flap and configured to rotate with the flap through the range of deployed positions. A forward fairing is rotatably connected to the aft fairing. The forward fairing acts as a counterbalance to the aft fairing and flap.

Abstract: A wheel well fairing for reducing drag on an aircraft fuselage configured with an open wheel well for stowing landing gear of the aircraft. The wheel well fairing includes a Coanda fairing having a convex-shaped lower portion and an upper portion. The upper portion is configured for positioning adjacent an interior vertically-orientated sidewall of the wheel well, and the convex-shaped lower portion has a bottom surface configured to extend substantially parallel to and positioned adjacent with an outer hull surface of the fuselage. The convex-shaped lower portion is curved inwardly within the wheel well between the upper portion and bottom surface. The Coanda fairing is positioned at an aft portion of the wheel well to redirect airflow out of the wheel well in a rearward direction along the bottom hull surface of the fuselage.

Abstract: A ducted fan propulsion comprises a duct with a cutout and a movable duct section that is moved between a retracted position within the cutout and am extended position relative to the duct. An actuator is disposed within the duct wall and is connected to the movable duct section with actuating linkage. A control linkage connects the movable duct section to the cutout edges. The movable duct section is extended when the ducted fan propulsion transitions from vertical takeoff to a level flight or transitions from level flight to a vertical landing. The movable duct section is retracted into cutout an becomes integrated with the duct during level flight.

Abstract: Rotor hubs having pitch control systems and related methods are disclosed herein. An example apparatus includes a housing including a first housing arm to support a first blade grip and a first blade spindle and a second housing arm to support a second blade grip and a second blade spindle. The example apparatus includes a first pitch link and a second pitch link. The example apparatus includes a first pitch arm coupled to the first pitch link and one of the first blade grip or the first blade spindle and a second pitch arm coupled to the second pitch link and one of the second blade grip or the second blade spindle. The second pitch arm is to extend past the first housing arm to couple with the one of the second blade grip or the second blade spindle.

Abstract: A propeller provided with interchangeable blades, and to a method of mounting such interchangeable blades on the propeller. The propeller comprises a hub, fastening fittings, rotation guide devices for guiding the fastening fittings in rotation relative to the hub, locking parts, and blades. The fastening fittings are configured to be assembled into the hub from the inside of the hub, and the locking parts lock respective ones of the fastening fittings onto the hub. The blades are fastened to respective ones of the fastening fittings outside the hub and can thus easily be replaced with other blades without removing the propeller.

Abstract: An aircraft wing is disclosed herein having a fixed-location trip device placed along the span of the wing to transition airflow from laminar flow to turbulent flow so that potential load increases are limited and flight performance uncertainties associated with laminar flow wings are reduced. Wings designed for extended laminar flow offer the potential to significantly reduce airplane drag and fuel consumption. A collateral impact of a laminar flow wing is the generation of elevated wing loads at critical load conditions. This impact is mitigated by controlling the downstream limit of transition at these critical load conditions.

Abstract: A landing gear system controller for controlling a landing gear system of an aircraft. The controller is configured to receive a request to operate a non-landing gear system element of the aircraft, and to cause operation of at least part of the landing gear system of the aircraft during a take-off or landing procedure on the basis of the request.

Abstract: A landing gear system for an aircraft is presented. The landing gear system comprises a composite flex beam having through-thickness stitching and a curvature having a radius greater than 5 inches; and a trunnion connected to the composite flex beam and offset from a neutral surface of the composite flex beam.

Abstract: A brake system for a vehicle is disclosed and includes an energy storage device configured to store and discharge energy, a plurality of wheels, one or more processors operatively coupled to the energy storage device, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the brake system to determine the brake system is operating in a backup mode of operation. In response to determining the brake system is operating in the backup mode of operation, the brake system calculates a dynamic slip of the plurality of wheels. The brake system is caused to determine a slip error by comparing the dynamic slip with a target slip value of the plurality of wheels. The brake system is also caused to calculate an antiskid command based on the slip error.

Abstract: A brake system for a vehicle is disclosed and includes an energy storage device configured to store and discharge energy, a plurality of wheels having an observer wheel, one or more processors operatively coupled to the energy storage device, and a memory coupled to the one or more processors. The memory stores data comprising a database and program code that, when executed by the one or more processors, causes the brake system to determine the brake system is operating in a backup mode of operation. In response to determining the brake system is operating in the backup mode of operation, the brake system is caused to apply a first brake pressure command to the observer wheel. In response to determining the observer wheel is starting the skid condition, the brake system is caused to determine a second brake pressure command based on a target slip value.

Abstract: A hybrid power tri-propeller helicopter apparatus for efficient and quiet flying includes a helicopter body, a cockpit portion, an engine portion, a tail boom portion, a gas motor, a generator, a battery pack, and an electric nose motor. A nose propeller and a lift propeller support are coupled to the helicopter body. A pair of electric lift motors is coupled to the lift propeller support and is in operational communication with the battery pack. A pair of lift propellers is coupled to the pair of lift motors. A tail fin and a pair of horizontal rear stabilizer fins are coupled to the tail boom portion. A pair of front stabilizer fins is coupled to the cockpit portion. A plurality of controls is coupled to the cockpit portion and is in operational communication with the nose motor, the pair of lift motors, and the pair of rear stabilizer fins.

Abstract: A thrust producing unit with a fail-safe electrical drive unit that drives a rotor of a rotary-wing aircraft. Fail-safe electrical drive unit may include input shafts, fixedly attached belt pulleys that are fixedly attached to the respective input shafts, output shaft that is coupled to rotor, freewheeling belt pulleys that are mounted to output shaft by means of respective freewheels such that output shaft rotates freely when output shaft rotates faster than one of the freewheeling belt pulleys belts that connect fixedly attached belt pulleys with the respective freewheeling belt pulleys, and electric motors that are coupled with the respective input shafts.

Abstract: In one embodiment, a drone is provided with several inflatable tubes that each connect a propeller component to a body of the drone. In order to increase the handling of the drone, a patch is placed on the top surface of each inflatable tube that includes some number of shape memory alloy wires. The shape memory alloy wires shrink and become rigid when an electric current is applied to them. The optimal locations on each tube to place the patches, and the shape of the patches, is determined using a topology optimization. Later, the wires in the patches can be selectively activated or deactivated by an operating entity to provide an additional means to control the drone. Additionally, the drone is equipped with several landing arms which may include a shape memory alloy torsion coil spring to help the arm deployment during landing.

Abstract: A rotor hub assembly that includes a yoke configured to attach blades thereto, a universal joint configured to attach to, and transmit forces between, a mast and the yoke, and an elastomeric member configured to attenuate vibrations transmitted from the universal joint to the mast.

Abstract: A VTOL aircraft (1), including: a fuselage (2) for transporting passengers and/or load; a front wing (3) attached to the fuselage (2); an aft wing (4) attached to the fuselage (2), behind the front wing (3) in a direction of forward flight (FF); a right connecting beam (5a) and a left connecting beam (5b), which connecting beams (5a, 5b) structurally connect the front wing (3) and the aft wing (4), which connecting beams (5a, 5b) are spaced apart from the fuselage (2); and at least two propulsion units (6) on each one of the connecting beams (5a, 5b). The propulsion units (6) include at least one propeller (6b, 6b?) and at least one motor (6a) driving the propeller (6b, 6b?), preferably an electric motor, and are arranged with their respective propeller axis in an essentially vertical orientation (z).

Abstract: A rotor blade control system and methods therefor including a hub assembly pivotally attached to a rotor blade; a mast attached to the hub assembly; a swashplate assembly engaged with the mast and including a swashplate actuation mechanism pivotally coupled with the non-rotating ring at a plurality of coupling locations for moving the non-rotating ring and pivotally coupled with the base at a plurality of base locations, the swashplate actuation mechanism comprises a plurality of substantially triangular dual actuator assemblies that are independently and concurrently operable to move the respective coupling location so as to impart movement on the non-rotating ring. The swashplate actuation mechanism is configured to move the swashplate assembly about a longitudinal axis and a lateral axis in response to a cyclic input. The swashplate actuation mechanism is configured to move the swashplate assembly along the mast in response to a collective input.

Abstract: Systems and methods for secure transportation and safe deployment of unmanned aerial vehicles are disclosed herein. An example method includes performing a UAV preflight procedure that includes determining UAV startup sounds from sound signals received from a microphone positioned within a housing that houses the UAV, determining synchronized rotation of propellers of the UAV, determining that no obstructions are present above the housing based on range finder signals; and releasing the UAV after completion of the UAV preflight procedure.

Abstract: Methods and systems are provided for responding to an attacker including a shooter who opens fire at a site where people are gathered, including identifying, neutralizing, and restraining the attacker. A system may include a central control unit configured to receive signals indicative of gun fire, to responsively determine an origin of the gun fire, to identify features of a shooter associated with the gun fire and to release a UAV from a shielded UAV housing to engage the shooter. The UAV may be configured to fly towards the shooter, according to the origin of the gun fire and the identifying features of the shooter, and to neutralize the shooter by operating a UAV incapacitating mechanism.

Abstract: A system and a method for providing service on a golf course using a fuel cell drone using a hydrogen fuel cell as a power source to provide various services while preventing a rounding delay of golfers are provided. A fuel cell drone of a system for providing service on a golf course may include a hydrogen fuel tank in which hydrogen is charged, a power pack configured to generate power to drive the fuel cell drone using the hydrogen in the hydrogen fuel tank, and a controller configured to move the fuel cell drone to a docking station or a gas supply place in response to determining that an amount of hydrogen remaining in the hydrogen fuel tank is below a set value.

Abstract: The subject matter described herein relates to aircraft designs and more particularly to aircraft designs using tandem wings and a distributed propulsion system. The embodiments described enable synergies between aerodynamics, propulsion, structure, and stability/control. In one embodiment, the tandem wings include a first wing set and a second wing set, each having a wing span with a set of thrustors placed along the wing spans.

Abstract: A deployable clasping system is configured to be deployed from a component and securely clasp and release an object. The deployable clasping system includes a cable that is deployable from the transit vehicle. A clasp assembly is coupled to the cable. The clasp assembly is configured to securely clasp the object. A propulsion sub-system is coupled to one or both of the cable and the clasp assembly. The propulsion sub-system is configured to maneuver the clasp assembly to the object.

Abstract: A cargo handling system is configured to load and unload a cargo container with respect to a cargo holding area of a vehicle. The cargo handling system includes parallel roller tracks extending from a floor. The roller tracks are separated by a clearance space. The roller tracks include rollers that are configured to rotatably support the cargo container. A mobile cargo mover is configured to move within the clearance space. The cargo mover is configured to engage the cargo container to move the cargo container on the roller tracks. The cargo mover is configured to disengage the cargo container to move away from the cargo container.

Abstract: Web pretensioning system devices for increasing the amount of web retracted by a given pretensioning stroke are disclosed. In some embodiments, the disclosed web pretensioning systems can include a pretension multiplier configured to receive a web of an aircraft passenger seat occupant restraint system. The pretension multiplier can include a web guide and a web coupling that is operably connected to a pretensioner. In operation, the pretensioner rapidly pulls or otherwise moves the web coupling away from the web guide a first distance, thereby retracting a loop of the web through the web guide. As a result of retracting the loop of web through the web guide, the overall retracted length of the web is equal to a second distance that is greater than the first distance.

Abstract: Arrangements for safety and comfort in vehicles.

Abstract: A seat assembly is configured to be positioned within an interior cabin of a vehicle. The seat assembly includes a seat support structure that is configured to connect to a floor structure within the interior cabin of the vehicle. The seat support structure includes a seat base and a front end opposite from a rear end. Arm rests are pivotally coupled to the seat support structure. A seat back is pivotally coupled to the seat support structure proximate to pivotal coupling of the arm rests to the seat support structure. In at least one other embodiment, a seat back coupling upwardly and rearwardly extends from a middle portion of the rear cross beam. A seat back includes a narrowed mounting portion that pivotally couples to the seat back coupling without interfering with knee space formed in a back side of the seat back.

Abstract: A braking table system for use in an aircraft cabin includes a rail mountable to a fixed structure in the aircraft cabin, the fixed structure adjacent a seat assembly, and, a table assembly mounted on and selectively movable along the rail. The table assembly includes a support deck engaged with the rail, a tabletop mounted on the support deck, and a braking mechanism carried by the support deck. The braking mechanism automatically engages the rail thereby preventing movement of the support deck relative to the seat assembly, and, upon user action moving the tabletop, the braking mechanism permits movement of the table assembly along the rail. The braking mechanism includes brake arms, each permitting movement of the table assembly in a respective direction, and, in the absence of user action moving the tabletop relative to the support deck, preventing opposite movement of the table assembly.

Abstract: An aircraft passenger seat construction capable of in-flight rocking motion and berthing, wherein rocking motion and berthing are mutually exclusive features. The seat construction includes a fixed frame including spaced frame members each having a support surface to be rocked on, a rocking frame including a seat pan and spaced rockers, the spaced rockers positioned to rock on the support surfaces, guides carried on the spaced rockers engaged to travel within guide slots of the spaced frame members, a backrest pivotally attached to the rocking frame, and a leg rest pivotally attached to the rocking frame. The rocking frame may rock back-and-forth in-flight or may be locked at any given position based on passenger preference. The seat construction is compatible with or without other seat adjustment mechanisms such as tracking, swivel, lie-flat and recline adjustment mechanisms.

Abstract: A device for unlocking a system for closing a container by means of a tie, such as a rope or strap, in particular a tie tensioned between closing eyelets, includes a cutting tool (O) capable of cutting the tie in order to unlock the closing system. It also includes an actuation member linked to the cutting tool, the actuation member being capable of being manipulated manually by a user in order to cause the cutting tool (O) to move into a position for severing the tie.

Abstract: An aircraft includes a compartment assembly having a blowout panel and a packboard configured to stow an evacuation system. The blowout panel may comprise a cover having a bracket mount and a bracket coupled to the bracket mount. The bracket may comprise a mating portion, a flange extending from the mating portion, a curved portion extending from the flange away from the blowout panel, and a lip portion extending from the curved portion opposite the direction of the curved portion. The packboard may comprise a slot configured to receive the bracket.

Abstract: An emergency escape slide container includes a first portion having a first end wall and a first side wall, the first side wall and the first end wall defining a first storage space that is sized and shaped to receive an emergency escape slide. The first side wall also includes a first rolling mechanism. The emergency escape slide container also includes a second portion having a second end wall and a second side wall, the second side wall and the second end wall defining a second storage space sized and shaped to receive the emergency escape slide. The second side wall also includes a second rolling mechanism. The first portion and the second portion cooperate to define a third storage space therebetween, the third storage space being equal to a combination of the first storage space and the second storage space.

Abstract: The invention relates to an unmanned aerial vehicle with an energy accumulator (20), which is connected releasably to a structural component (29) of the aerial vehicle, and with an accumulator plug (32), via which electrical energy is conducted from the energy accumulator (20) to a rotor drive (18) of the aerial vehicle. In an operating position, a locking element (25) locks the energy accumulator (20) in relation to the structural component (29) and, in a maintenance position, releases the energy accumulator (20), wherein a full engagement of the accumulator plug (32) is blocked at the same time. The invention also relates to an energy accumulator for such an aerial vehicle, and to a method for attaching an energy accumulator to such an aerial vehicle. It can easily be checked by means of the invention whether the energy accumulator has been attached correctly.

Abstract: Methods and apparatus for cooling a surface on a flight vehicle and/or generating power include advancing the flight vehicle at a speed of at least Mach 3 to aerodynamically heat the surface. A supercritical working fluid is circulated through a fluid loop that includes compressing the supercritical working fluid through a compressor, heating the supercritical working fluid through a heat intake that is thermally coupled to the surface, expanding the supercritical working fluid in a thermal engine to generate a work output, cooling the supercritical working fluid, and recirculating the supercritical working fluid to the compressor. The work output of the thermal engine is operably coupled to the compressor, and may optionally be coupled to a generator to produce power. The supercritical working fluid absorbs heat from the surface, eliminating hot spots and permitting use of lighter and/or less expensive materials.

Abstract: An inerting system includes a fluid circuit, a reactor within the fluid circuit, at least one particulate removal device (PRD) downstream from the reactor, and a fluid tank. The fluid tank is downstream from the at least one PRD. A method for removing particulates from a fluid stream in a fluid circuit includes receiving a fluid stream in a reactor within a fluid circuit, outputting an exhaust stream from the reactor, receiving the exhaust stream in at least one PRD downstream from the reactor, removing particulate from the exhaust stream, and receiving the exhaust stream with particulate removed in a fluid tank downstream from the at least one PRD.

Abstract: A power supply unit includes a housing having at least one input terminal and at least one output terminal, an AC-DC converter which is arranged in the housing and which is connected to the input terminal, a DC-DC converter which is arranged in the housing and which is connected to the output terminal; and a capacitor which forms a structural part of the housing. Furthermore, an on-board power supply network of an aircraft or spacecraft is also described.

Abstract: A system includes an aircraft avionics system and a portable computing device. The aircraft avionics system is configured to run one or more embedded avionics applications. The portable computing device is in operable communication with the aircraft avionics system and is configured to run one or more portable device applications. Each portable device application has resident therein a software development kit having libraries and utilities that enables the portable device application to: establish a secure connection with the aircraft avionics system, establish and maintain a required protocol with the embedded avionics application, and communicate with the embedded avionics application as specified by an application programming interface definition.

Abstract: An aerodynamic blade is provided and includes a blade body and a light module. The blade body includes an inboard end and a tip outboard of the inboard end. The blade body is connectable with a hub at the inboard end such that rotations of the hub drive rotations of the tip about a rotational axis. The light module is disposed in the tip and configured to activate in response to the rotations of the tip about the rotational axis to emit light visible at an exterior of the blade body.