Abstract: A snow vehicle includes a frame comprising an upper frame portion and a lower frame portion, a handlebar comprising a handlebar axis, said handlebar coupled to said upper frame portion and said lower frame portion and a tunnel comprising having a driven track shaft and a track rotatably coupled to the driven track shaft within the tunnel. A two-stroke engine includes a crankshaft and a tuned pipe coupled to the engine. The engine and the tuned pipe are positioned between the handlebar axis and the driven track shaft. A continuously variable transmission is disposed between the handlebar axis, the upper frame portion of the frame and the lower frame portion.

Abstract: A watercraft, in particular a SWATH-type yacht is intended to have improved and greater functional properties. To this end, the watercraft, in particular a SWATH-type yacht, has upper works that receive a structure, and on the underside thereof, i.e. the wet deck, two stilts, i.e. partial hulls are arranged which are spaced apart from one another transversely in the direction of travel. Each partial hull is positioned on a submerged hull which is arranged substantially in the direction of travel of the watercraft and extends over at least part of the upper works. The submerged hulls have characteristic narrowed portions in cross section, which portions are formed on the longitudinal extension of swimmer profiles of the partial hull.

Abstract: The invention relates to a floating structure, comprising a plurality of interconnected frames and a plurality of buoyant members supporting the structure, wherein the frames are substantially triangular in planform. Adjacent triangular frames may be movably connected, in particular pivotably connected. The triangular frames may comprise right-angle triangles, isosceles triangles or equilateral triangles. The floating structure may support an installation, like e.g. a solar farm. The invention also relates to a triangular frame for use in such a floating structure.

Abstract: A device for reducing hydrodynamic drag of a vessel including a hull; a fuel cell, and a system of conveyance of a first amount of air discharged by the fuel cell to at least one system of injection included by the hull, the system of injection being configured to inject the first amount of air opposite a surface of the hull intended to be immersed.

Abstract: A mooring apparatus may allow for watercraft to be secured to a mooring structure. An example of a mooring apparatus includes a frame secured to a shell cover at a plurality of points, a plurality of rollers disposed within the frame, and a tension bar disposed within the frame and parallel to the plurality or rollers.

Abstract: A system for docking a boat on a body of water includes a pole or shaft mounted with respect to the bed of the body of water and extending above the surface of the body of water. A locking spacer is slidably connected to the pole. A member has an outer surface and an inner surface defining a cavity that is open at two ends. The member also defines a slot extending from the outer surface to the inner surface. The member is mounted to a boat. The system enables the rapid and easy mooring of the boat by maneuvering the boat so that the pole passes through the slot and into the cavity. The locking spacer is then slid along the pole until it enters the cavity, thereby locking the member with respect to the pole.

Abstract: A mooring system includes a floater, a first anchor, a first mooring line, and a second mooring line. The first mooring line and the second mooring line are each connected to the first anchor and extend to the floater. The first mooring line is connected to the floater at a first connection point. The second mooring line is connected to the floater at a second connection point. The first connection point is spaced apart from the second connection point.

Abstract: A mooring system includes a floater, a first anchor, a first mooring line, and a second mooring line. The first mooring line and the second mooring line are each connected to the first anchor and extend to the floater. The first mooring line is connected to the floater at a first connection point. The second mooring line is connected to the floater at a second connection point. The first connection point is spaced apart from the second connection point.

Abstract: Disclosed is a method for controlling a hydrofoil board powered by a motor driven propeller. The motor is controlled by a hand controller configured with user selectable operating pre-sets including a first operating pre-set, wherein the board is accelerated to a first speed which is less than that required for the board to hydrofoil, and a second operating pre-set, wherein the board is accelerated to a second speed sufficient for the board to hydrofoil. Alternatively, the operating pre-sets may limit the motor power. A system for operating a hydrofoil board is also disclosed, which includes a propulsion control unit comprising a propulsion source, and a hand controller configured to receive a first user input and a second user input and to transmit the user inputs to the propulsion control unit.

Abstract: A bending method for an inflatable kayak bottom includes: step 1: cutting the fabric; step 2: sewing and locking; step 3: performing air seal installation in a hole zone; step 4: performing air seal installation around a drop stitch material and placing a nozzle; and step 5: bending into shape, the inflatable kayak bottom becoming airtight overall. In the present application, the drop stitch material of the kayak bottom is sewn and locked to make a deformable kayak bottom structure, which features low costs, easy use and high practicality.

Abstract: A double-chambers inflatable kayak, including an upper chamber and a lower chamber which are fixedly connected to each other by a connecting portion and between which a cavity is formed, wherein the upper chamber includes a cockpit hole and a first air valve provided on the surface, the cockpit hole being in communication with the cavity, and the first air valve being used to inflate and deflate the upper chamber, and wherein the lower chamber includes a second air valve which is used to inflate and deflate the lower chamber.

Abstract: Disclosed systems, devices, and methods support an automated dynamic way to reversibly span the surface of a waterway, and may include deploying a floating boom and catch bin to redirect and capture floating waste before it reaches the terminus of the waterwaye; detecting, by a sensor suite, impending boat traffic; activating, by a control system, one or more actuating line motors for one or more closing lines; verifying, by the control system, a closed configuration; verifying, by the control system, whether a battery bank charge is above a required threshold, where if the battery bank charge falls below the required threshold then the system remains in the closed configuration; activating, by the control system, one or more actuating line motors for one or more opening lines if the battery bank charge is above the required threshold; and verifying, by the control system, an open configuration of the system.

Abstract: A system for a boat includes a first guideway installed under a main deck of the boat, a first battery pack coupled to the first guideway under the main deck, and a first actuator configured to move the first battery pack along the first guideway. A controller is electrically and/or signally coupled with the first actuator. A user input device is electrically and/or signally coupled with the controller. The controller is configured to control the first actuator to move the first battery pack along the first guideway in response to an input to the user input device so as to relocate the weight of the first battery pack under the main deck.

Abstract: A marine vessel advisory system may be configured to calculate and provide operational information that show fuel consumption savings based on adjustment of vessel speed and/or heading. In an embodiment, the advisory system may operate real-time to collect operational and/or environmental conditions information to be used to calculate alternative operational performance of the marine vessel that will save fuel and reduce emissions. The calculations may include a simulation, machine learning, and/or artificial intelligence to determine a speed and/or heading of the marine vessel that will reduce fuel consumption. The advisory system may display the computed information for the operator, and the operator may elect to switch to the alternative operating parameters (e.g., slower speed).

Abstract: A method of three-dimensional fabrication of an object is disclosed. The method comprises: forming a plurality of layers in a configured pattern corresponding to the shape of the three-dimensional object, at least one layer of the plurality of layers being formed at a predetermined and different thickness selected so as to compensate for post-formation shrinkage of the layer along a vertical direction. In various exemplary embodiments of the invention spread of building material of one or more layers is diluted at least locally such as to maintain a predetermined thickness and a predetermined planar resolution for the layer.

Abstract: A trolling motor mount assembly for mounting a trolling motor to a small watercraft. The assembly includes a motor mount piece and a boat deck piece. The pieces are shaped to mate their cooperatively tapered sides to securely engage the pieces and thus the mounted motor and boat together. A latch then locks the pieces together.

Abstract: The technology relates to techniques for drogue deployment for a lighter than air (LTA) vehicle descent. A drogue deployment system for an LTA vehicle descent can include a drogue comprising a drogue parachute coupled to a carrier. A spring can be configured to launch the drogue from a launch tube directed outward from an apex of the LTA vehicle in an acute angle from a horizontal plane. A core can be placed around the launch tube and placed around the spring, the core compressing the spring and holding the spring in a compressed state prior to deployment, and a riser can couple the carrier to the envelope of the LTA vehicle. In some cases, the drogue deployment system can comprise two or more drogues, wherein intervals between the two or more drogues can be selected such that horizontal components of drogue deployment forces approximately cancel out.

Abstract: An altitude control system for an unmanned aerial vehicle includes a compressor assembly defining a plenum therein, a passive valve assembly coupled to a first portion of the compressor assembly and in fluid communication with the plenum, and an active valve assembly coupled to a second portion of the compressor assembly and in fluid communication with the plenum. A method of controlling an altitude of an unmanned aerial vehicle and an unmanned aerial vehicle are also provided.

Abstract: A method and system for processing parameter values from a redundant sensor configured to sense a parameter used in the control of an aircraft engine is provided. The method includes: a) receiving a plurality of parameter values from a redundant sensor by sensing the same parameter at the same time; b) identifying mismatched parameter values; c) producing a predicted parameter value using an artificial intelligence (AI) model having a database of parameter values representative of the sensed parameter; d) providing the predicted parameter value to a control unit; and e) operating the control unit to select a first parameter value or a second parameter value using the predicted parameter for use in the control of the aircraft engine.

Abstract: An aircraft wing (1) provided with a trailing edge region (2) which is provided with a noise attenuation structure, which at least comprises in combination, looking in an upwards direction: a first micro perforated plate (2.1) with micro perforations, a structure (2.2) with open channels, a second micro perforated plate (2.3) with micro perforations, and a third micro perforated plate (2.4) with micro perforations, wherein the open channels of the structure (2.2) connect micro perforations of the first micro perforated plate (2.1) with micro perforations of the second micro perforated plate (2.3), and that at least one of the second micro perforated plate (2.3) and the third micro perforated plate (2.4) is slidable with respect to the other for aligning and/or misaligning the micro perforations of the second micro perforated plate (2.3) and the third micro perforated plate (2.

Abstract: A supersonic flow system in which a supersonic flow is encountered includes a surface configured to be exposed to a supersonic fluid flow, wherein the surface includes an upstream end and a downstream end opposite the upstream end, a wave generator coupled to the surface and including one or more actuators configured to selectably induce strain in the surface, and a wave controller in signal communication with the wave generator and configured to activate the one or more actuators to induce one or more travelling waves configured to travel along the surface between the upstream end and the downstream end of the surface.

Abstract: A powered clutch actuator assembly for integration with a clutch assembly is provided. The actuator and clutch assemblies, sized to fit within constraints of an aircraft landing gear wheel-mounted taxi drive system, are engineered to occupy a default neutral disengaged position that prevents torque transfer when torque to move the aircraft should not be transferred to the taxi drive system. Multiple solenoids and diodes power rotational motion of the actuator assembly to move a bi-directional clutch component in a desired rotational direction during torque transfer. A locking solenoid automatically locks and maintains the actuator assembly in a neutral disengaged condition when none of the solenoids are powered and disengages the actuator assembly when one solenoid is powered to cause rotation of the actuator assembly. Solenoid supports structured to operate as integral heat sinks may direct heat to an on-aircraft heat sink, prolonging the working life of the actuator assembly.

Abstract: A braking device for braking a wheel of an aircraft, a hub of which is mounted rotatably on an axle includes a stack of discs threaded on a torque tube which is attached to the axle and equipped internally with a heat shield extending opposite an outer surface of the hub facing the stack of discs to protect the hub from heat radiation generated by the stack of discs. The heat shield includes a tubular body which is coaxial to the torque tube and retaining tabs which are resiliently deformable and secured to the tubular body, each of the retaining tabs and an inner surface of the torque tube including additional raised portions to engage with one another so as to axially immobilize the heat shield inside the torque tube.

Abstract: A commanded control signal is compared against an adaptive control signal in order to detect a rotor strike by a rotor included in an aircraft, wherein the adaptive control signal is associated with controlling the rotor and the adaptive control signal varies based at least in part on the commanded control signal and state information associated with the rotor. In response to detecting the rotor strike, a control signal to the rotor is adjusted in order to reduce a striking force associated with the rotor.

Abstract: A method of modifying a rotor blade is provided for a rotor blade including a spar having an inboard portion with a substantially constant overall height, the inboard portion further including a top layer having a substantially constant first thickness and a bottom layer having a substantially constant second thickness. The method includes removing a root portion of the inboard portion to thereby modify the rotor blade and installing a cuff configured to couple to the rotor blade to an aircraft.

Abstract: An aircraft comprises a fuselage, first and second wing segments each having a leading edge and a trailing edge, a plurality of spokes coupling the fuselage to the first and second wing segments, one or more motors disposed within or attached to the plurality of spokes, and three or more propellers proximate to a leading edge of the plurality of spokes, distributed along the plurality of spokes, and operably connected to the motors to provide lift whenever the aircraft is in vertical takeoff and landing and stationary flight and provide thrust whenever the aircraft is in forward flight. When the aircraft is in vertical takeoff and landing and stationary flight, the fuselage is approximately vertical. When the aircraft is in forward flight, the fuselage is approximately in the direction of the forward flight and extends forward beyond the leading edges of the first wing segment and the second wing segment.

Abstract: A control device 133 acquires distance information indicating a distance between an UAV 1 and an article B positioned under the UAV 1 and controls a winch 16 to unreel a linear member 15 on the basis of the distance indicated in the acquired distance information.

Abstract: The present invention provides a fixing system to connect, install, mount and/or fix a device or an equipment to a structure or a structural environment such as, for example, an aircraft structure, through at least one first fixing means and at least one second fixing means. Furthermore, the present invention relates to a method for using such a fixing system in a method for connecting, installing, mounting and/or fixing a device or an equipment to a structure or a structural environment such as, for example, an aircraft structure to a structure of the aircraft and to a device. The fixing system can be a bracket. The fixing system comprises at least one first fixing means to connect a structure or a structural environment to the fixing system and at least one second fixing means to connect a device or an equipment to the fixing system.

Abstract: A hybrid water storage system for an aircraft includes separate variable volumes for respectively storing/holding potable water and gray water occupying a common container. The hybrid water storage system is generally configured to draw potable water from a first variable volume in order to provide fresh water to one or more aircraft appliances (e.g., sinks, showers, ice-makers, etc.), and the used potable water (i.e., the potable water that is collected in drains from the aircraft appliances), referred to herein as gray water, is routed to a second variable volume that occupies the same container as the first variable volume.

Abstract: A connecting link for connecting first and second components such as an aircraft seat leg and a track fastener. The link includes a helical middle portion forming an interior space in which an energy attenuator is positioned. In embodiments, the energy attenuator includes inner and outer cylindrical bodies that operate in translation upon a deformation of a lattice structure configured to deform when at least one of a compressive threshold and a tensive threshold is met. In embodiments, the energy attenuator receives part of one of the first and second components. The connecting link may be manufactured by an additive manufacturing process and used in an aircraft leg assembly to save weight and absorb impact energy on the leg.

Abstract: A method determines the position of an actuating device of an element of an aircraft seat. The actuating device includes a calculating unit, an actuator movably mounted on an output shaft for actuating the element, the output shaft being connected to an angular position encoder so a position (X) of the actuator on the output shaft corresponds to a single angular position (?) of the encoder. The method includes a preliminary submethod of automatically calibrating the actuating device including: placing the actuator at a predetermined position (Xref) corresponding to an expected angle value (?att) of the encoder; measuring an initial positioning angle value (?ini) of the encoder when the actuator shaft is in the predetermined position (Xref); comparing the initial positioning angle value (?ini) and the expected angle value (?att) calculating the angular offset of the encoder signal, with ?décal=(?ini??att) [MODULO 360°], ?decal being between 0° and 359°.

Abstract: A passenger seat row, for a vehicle such as a passenger aircraft, convertible between passenger seats and bunk beds. The passenger seat row includes a frame assembly including a backrest extending substantially a length of the frame assembly, the backrest configured to move between a stowed condition against the frame assembly and a deployed condition forming a substantially horizontal bed. Armrests attached to the frame assembly reposition to support the bed when in the deployed condition. In use, deploying the backrest forms a first bed positioned over the second bed to form a bunk bed sleeping provision for use, for example, during flight.

Abstract: A passenger seat including a sleep support system attached to a backrest of the seat and including first and second support arms pivotally attached to respective first and second sides of the backrest configured to deploy forward. A pillow assembly attaches to the deployed first and second support arms and a tubular cover is positioned surrounding at least a portion of the pillow assembly. In use, a seated passenger deploys the arms forward, attaches the covered pillow assembly, and leans forward against the pillow to assume a comfortable sleeping position.

Abstract: A method for manufacturing a profile rail including a base made of a first material and a top portion to be exposed during use of the profile rail in the floor of a vehicle including a second material that is harder and/or less corrosive as the first material. The method includes the steps of providing the base made of the first material, coating at least the top portion of the base with the second material by a cold spray process, and machining the coating to provide a predefined surface structure of the top portion.

Abstract: A cooling system of a vehicle includes an inlet for receiving a medium. A turbine is fluidly connected to the inlet. A coupling mechanism is operably coupled to the turbine by a shaft. The medium is ram air.

Abstract: An aircraft air conditioning system comprises intakes ram air from outside the aircraft, and uses a heat exchanger to pretreat (preheat or precool) some of the ram air. The system further includes a heat recovery unit that uses the cabin exhaust air to further heat the pretreated ram air, resulting in conditioned ram air. The system further includes an air conditioning pack unit to produce a first conditioned air stream from the conditioned ram air. The system further includes a mixing box to mix the first conditioned air stream with another subflow of ram air to produce a second conditioned air stream.

Abstract: A latch mechanism is provided that includes a latch housing, latch keeper, and a latch hook adjustment assembly. The latch hook adjustment assembly includes a latch frame, latch handle, hook member, bearing block, a nut, and a spring member. The latch frame has a front wall, an interior wall, and a forward cavity. The hook member has a partially threaded shaft. The bearing block has a flange, indexing features, and a bore. The flange has opposing first and second side surfaces. The indexing features project outwardly from the second side surface and are disposed adjacent the bore. The nut has first and second axial end surfaces, a threaded nut bore, and index cavities disposed in the first axial end surface adjacent the nut bore. The bearing block, nut, and spring member are disposed in the forward cavity. The latch hook adjustment assembly is disposable in engaged and disengaged configurations.

Abstract: Said device (16) for controlling an electrical thrust reverser control system (1) for an aircraft comprises electrical supply means (9) and control means (19) which are configured to couple the electrical supply means (9) to the electrical control system (1) when the aircraft is on the ground and to uncouple the electrical supply means (9) from the electrical control system (1) when the aircraft is flying.

Abstract: A controller (a control unit) of a power supply system of a vertical take-off and landing aircraft is configured to: after lift is generated by wings (a front wing and a rear wing), perform stop control of controlling electric power supplied to a motor so that rotation of a VTOL rotor continues to stop; temporarily cancel the stop control in response to the temperature of any one switching element detected by a temperature detection unit (a temperature sensor) becoming equal to or higher than a temperature threshold during the stop control; and resume the stop control after the stop control has been temporarily canceled.

Abstract: An aircraft engine, has: an inlet leading to a compressor section, the inlet extending circumferentially around a central axis; an annular inlet duct extending circumferentially around the central axis, the annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet, the duct outlet extending circumferentially around the central axis; and a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct, being movable within the annular inlet duct along a circumferential direction relative to the central axis in response to a fluid pressure differential on opposed sides of the flow restrictor.

Abstract: A cooling system (10) for an aircraft is provided, in particular for cooling at least one element of an electric propulsion system (24) of the aircraft, the cooling system (10) being at least partially disposed within a wing (12) of the aircraft and including at least two heat exchangers (16, 42) interconnected via at least one cooling circuit (11), the first heat exchanger (16) being operatively connected to the at least one element to be cooled of the electric propulsion system (24), and the second heat exchanger (42) being disposed within at least one wing (12) and being operatively connected to an upper and/or lower wing shell (46, 48) of the wing (12). A method for cooling at least one element of an electric propulsion system (24) of an aircraft is also provided.

Abstract: Hybrid-electric powertrains for aircraft are disclosed herein. An example hybrid-electric powertrain includes a gas turbine propulsion engine including a first propulsor and a gas turbine engine to drive the first propulsor to produce thrust, a generator operably coupled to a drive shaft of the gas turbine engine, and an electric propulsion unit including a second propulsor and an electric motor to drive the second propulsor to produce thrust. During a first mode of operation, the gas turbine propulsion engine and the electric propulsion unit are activated to produce thrust, and the generator is driven by the gas turbine engine to produce electrical power to power the electric propulsion unit. During a second mode of operation, the gas turbine propulsion engine is activated to produce thrust and the electric propulsion unit is deactivated.

Abstract: A propulsion assembly for an aircraft comprising at least two electric motors configured to be disposed in a wing of the aircraft and each comprising a rotor having a motor shaft movable about a motor axis, at least one propeller borne by a propeller shaft movable about a propeller axis and mechanically coupled to the motor shaft of the at least two electric motors, the propeller axis being perpendicular to the motor axis of the at least two electric motors.

Abstract: Disclosed is a fuel conditioning system (SC) configured to supply an aircraft turbine engine using fuel (Q) from a cryogenic tank (RC), the conditioning system (SC) comprising at least one pumping turbomachine (1), a first heat exchanger (31) configured to heat the fuel (Q) in the fuel circuit (CQ) by circulating an air stream (A), and at least one heating turbomachine (2) configured to supply an air flow (A) to the first heat exchanger (31), the heating turbomachine (2) comprising an air intake compressor (21), a combustion chamber (24) and an air exhaust turbine (22) configured to drive the air intake compressor (21), the combustion chamber (24) being supplied with air taken from the air flow (A) and with the fuel (Q) from the fuel circuit (CQ).

Abstract: Disclosed herein is a detachable modular console for an aircraft cockpit. The detachable modular console comprises a housing configured to receive one or more modular electronic components, a plurality of hardpoint fasteners for detachably fastening the housing to hardpoints in a floor of the aircraft cockpit, a leveling foot to engage the floor to stabilize the console and a display screen supported by the housing. The detachable modular console can house various modular electronic components. A rail enables rapid replacement of other electronic components. The hardpoints enable the console to be secured to the floor of the cockpit.

Abstract: Examples described herein provide a method for aircraft engine anomaly detection based on an odor. The method includes receiving data indicative of the odor associated with an aircraft engine of an aircraft. The method further includes analyzing the data to determine whether an anomaly associated with the aircraft has occurred. The method further includes responsive to determining that an anomaly associated with the aircraft has occurred, implementing a corrective action based at least in part on the data.

Abstract: In an example embodiment, a drone-based system comprises: a base station, wherein the base station is configured to provide drone control and power, a drone; a tether connecting the base station to the drone and configured to provide the drone with the power from the base station; and a lighting system, operably attached to the drone via the tether, configured to generate illumination of a ground area, wherein the illumination of the ground area is controllable by modifying least one of an intensity of the illumination and a height of the drone above the ground area.

Abstract: An example carriage is configured for mounting to an unmanned aerial vehicle. The carriage generally includes a housing assembly configured for mounting to the unmanned aerial vehicle, a movable grip mounted to the housing assembly for movement between a capturing position and a releasing position, a latch device, and a driver. The latch device has a latching state and an unlatching state, is configured to retain the movable grip in the capturing position when the latch device is in the latching state, and is configured to permit movement of the movable grip from the capturing position to the releasing position when in the unlatching state. The driver is operable to transition the latch device from the latching state to the unlatching state.

Abstract: An unmanned aerial vehicle according to certain embodiments generally includes a chassis, a power supply mounted to the chassis, a control system operable to receive power from the power supply, a plurality of arms extending outward from the chassis, a plurality of rotors, and a support structure mounted atop the chassis. Each rotor is mounted to a corresponding arm of the plurality of arms, is in communication with the control system, and is operable to generate lift under control of the control system. The support structure includes a plurality of arched struts that connect to one another at an apex region of the support structure.

Abstract: In an aircraft monitoring system for monitoring a fuselage of an aircraft, an imaging device mounted to the fuselage is configured to capture and acquire at least images of driven parts involved in generation of lift or thrust for flight of the aircraft. An image processor is configured to use the captured images to generate an overhead image of the aircraft as viewed from above the fuselage.