Abstract: Methods for controlling tension in mooring lines of a floating offshore structure having a buoyancy structure including one or more water tanks and the buoyancy structure providing excess buoyancy are provided. The methods comprise varying the mass and/or the centre of gravity of the floating offshore structure by varying the quantity of water in one or more of the water tanks. Also, floating offshore structures are disclosed, the structures comprising a buoyancy structure having one or more floater tanks providing excess buoyancy, and a plurality of tensioned mooring lines, and further comprising a control system for increasing and decreasing a quantity of water in one or more of the floater tanks. Also, possible uses of floating offshore structures are provided wherein under standard operating conditions, the floater tanks are at least partially filled with water.

Abstract: The invention relates to a holding device for fastening, to the stem area of a ship, a ship's boat or an additional component to be detachably carried along, which device comprises a plurality of arms which have a hook-shaped coupling and are rigidly or detachably connected to the ship's boat or additional component, and a plurality of receiving portions which comprise at least one coupling shaft and are mounted on the stem or on an additional part of the ship permanently installed on the stem in such a way that the arms are hooked into the coupling shaft by the hook-shaped coupling and by a rotation of the arm or the receiving portion about the coupling shaft are locked in place when a defined angle of rotation is reached.

Abstract: A multiple position automated convertible V-berth system for marine vessels having a pair of independent bunks sections, and guide mechanisms for controlling the physical movement of the bunks from one configuration to another. Included is automatic actuation and electronic controls for activating movement of the bunks from one configuration to another in conjunction with the guide mechanism. The multiple position automated convertible V-berth system is convertible between a V-berth configuration and an island bed configuration, eliminates manual operation, and includes automatic deployment and retraction of a table.

Abstract: A floating type self-lifting drilling platform includes a main deck, a floating cushion, pile legs, a lifting mechanism and a mooring system. The area and thickness of the floating cushionare both greater than those of the main deck, the middle part is provided with a moon pool, and the inner part is partitioned into multiple cabins; there are three pile legs, the pile legs are truss structures, the bottom part of each of the pile legs is rigidly connected with the floating cushion, and the main deck lifts vertically along the pile legs through the lifting mechanism and is fixed at a preset height; each pile leg includes upper and lower hollow sealing bodies; the water line is located in the height range of the upper section during the operation and positioned through the mooring system.

Abstract: A universal bracket allowing secure attachment of accessories to paddleboards or similar watercraft. Said bracket consists of two identical assemblies of three components. The first is a rectangular plastic tube that rests on the top surface of the paddleboard. Said tube is open at each end and acts as a receiving tube for two smaller rectangular plastic tubes. The smaller tubes each having a molded hook on one end that attaches to the outer edges of the paddleboard. The width of the assembly is adjustable to accommodate varying paddleboard sizes. The adjustable nature is such that the outer tubes slide freely into the center tube and are locked in place by a removable pin. The pin locking system allows for customization and a variety of settings. The center receiving tube contains a mechanism for securing accessories that expand the capabilities of a paddleboard.

Abstract: In some aspects of the disclosure, an attachable lighting device has a lighting assembly which includes a light housing, an attaching base, and one or more optical sources. The light housing is attached to the top of the attaching base and contains the one or more optical sources. The attachable lighting device has a receiving base which is attachable to an attachment surface of a boat. The attaching base is attachable to the receiving base.

Abstract: A terminal device stores ship characteristic data that indicates a relationship between rotation speed and ship speed, and rotation speed and fuel consumption when a ship is navigated under various navigation conditions. If a user inputs data that indicates draft state and wind and wave state on a performance display screen displayed on the terminal device, the terminal device generates relationship data that indicates a relationship between rotation speed and ship speed, and rotation speed and fuel consumption when a ship is navigated under wind and wave states corresponding to the input data and each of a plurality of Beaufort states that are set in the terminal device in advance on the basis of the ship characteristic data. The terminal device displays a graph that displays the relationship between rotation speed, ship speed and fuel consumption for each of a plurality of navigation conditions using the relationship data.

Abstract: A lifesaving bag includes: a band, including a first side, a second side, a head end engaging section and a rear end engaging section; a zipper group, including a first zipper portion disposed at the first side, a second zipper portion disposed at the second side, and a zipper head adapted for engaging and disengaging the first zipper portion and the second zipper portion; a bottom portion, fixed with the rear end engaging section; a head portion, fixed with the head end engaging portion. When the first zipper portion and the second zipper portion are engaged, the band forms a hollow body, and the head portion and the bottom portion enclose upper and lower ends of the hollow body to form a bag. When the first zipper portion and the second zipper portion are disengaged, the band becomes a long strip-like rescue rope.

Abstract: Systems and methods for buoyancy compensation are provided. Both active and passive buoyancy compensation can be provided using a compressible mixture made of a liquid along with a hydrophopic material such as a powder, electrospun fiber, or foam. The compressible fluid compresses as pressure is applied or expands as pressure is released thereby substantially maintaining an overall neutral buoyancy for a vessel. This allows the vessel to ascend and descend to water depths with minimal active buoyancy change. As a result, the energy usage and the reliance on higher pressure air and oils can be minimized.

Abstract: An underwater watercraft including a passenger compartment and an ingress egress port in which the watercraft has buoyancy and center of gravity adjusted to maintain a generally level or other desired attitude when submerged, and an angled attitude at a water surface for ingress/egress. The attitude also is adjustable via the placement of ballast and optionally including a movable ballast that adjusts the location of the center of gravity as desired. The ingress-egress port optionally includes an entry elevated from a main passenger compartment, that has an angled orientation in a submerged mode, and an optional orientation generally parallel to the water surface in a surface mode.

Abstract: The present invention is directed to a modular azimuth thruster (1) for propelling a vessel, having a thruster housing (1) around which water flows, and comprising: a standardized core unit (2) having a core unit housing (21) forming part of the thruster housing, a transmission line (6) arranged within in the core unit housing (21), comprising a propeller shaft (61) extending in a longitudinal direction (13) of the thruster housing, and a propeller (3) arranged outside the thruster housing and being operationally connected to the propeller shaft. The present invention further relates to a vessel comprising an azimuth thruster and a method of configuring an azimuth thruster.

Abstract: A sailcloth including at least one textile layer, wherein at least one textile layer consists of a nonwoven fabric material with unidirectionally or bidirectionally aligned filaments.

Abstract: A deflector control portion in a jet propulsion boat causes a deflector to swing by controlling a deflector drive mechanism in response to an operation of a shift operating portion. The deflector control portion causes the deflector to move to a first trim position when the shift operating portion is switched to a forward movement shift position. The deflector control portion causes the deflector to move to a second trim position when the shift operating portion is switched to an operating shift position.

Abstract: A watersports paddle includes an elongated handle body having a first material, a biased member having a second material more flexible than the first material such that the biased member is more flexible than the elongated handle body, and a paddle blade coupled to the biased member opposite the elongated handle body. The biased member deforms when a force is applied to the biased member with the elongated handle body by pulling the paddle blade through water and reforms when the force is not applied to the biased member by the elongated handle body to store and release energy during use of the watersports paddle. The biased member may be a substantially planar leaf spring or a bowed leaf spring.

Abstract: In an outboard motor equipped with a V-type four-cycle engine provided with a left bank extending leftward and obliquely rearward and a right bank extending rightward and obliquely rearward, a drive shaft is perpendicularly disposed in the outboard motor body so as to transmit a driving force from the engine to a propeller disposed below the engine, and center positions of the left side exhaust passage and the right side exhaust passage are positioned forward than the drive shaft in a front-and-rear direction in an advancing direction of the outboard motor.

Abstract: An outboard drive device (10) comprising a motor (11) having a crankshaft (16), wherein said outboard drive device (10) further comprises a propeller shaft (12) with a propeller which propeller is below the hull (13) of a boat when said outboard drive device (10) is operated, and a power coupling system for transferring power from the motor (11) to the propeller shaft (12). The motor (11) is an automotive motor or an industrial base engine, wherein the crankshaft (16) is substantially horizontal and substantially parallel to the propeller shaft (12) when said outboard drive device (10) is operated. The power coupling system comprises a power transfer device (17), a transmission (18) and a transmission drive shaft (19). The power transfer device (17) connects the crankshaft (16) with the transmission drive shaft (19) for transferring the output power from the crankshaft (16) to the transmission drive shaft (19).

Abstract: Disclosed herein is a motorized kayak comprising: a hull; a hatch; a motor; a pump; a controller; and one or more batteries; wherein the hull and hatch create a water and air tight seal and the position of the batteries is adjustable to change the center of gravity.

Abstract: A vehicle control device is provided. The device includes a target bearing calculating module configured to calculate a target bearing of a vehicle based on a direction of a disturbance, a stern bearing calculating module configured to calculate a stern bearing, and a rudder mechanism drive signal determining module configured to determine a rudder angle command so that the stern bearing approaches the target bearing, and determine a rudder mechanism drive signal based on the rudder angle command.

Abstract: Improvements in an emergency inflatable signal locator is disclosed the emergency inflatable signal locator is a portable self-contained emergency inflatable illuminated signal location indicator generally provides a carrying case defining an interior volume carrying a container of compressed helium and an inflatable balloon having a reflective exterior surface and carrying a light source, the inflatable balloon connected to one end of a length of tether. The tether having a second end portion securely fastened to a reel that is securely interconnected to the interior of the carrying case allowing the inflated balloon to be retracted if necessary.

Abstract: An aircraft tail cone comprising a fuselage in which avionic equipment is housed. The tail cone comprises two lateral hatches formed in the fuselage, at least one hatch being formed on each of the two opposite sides of the fuselage. Each hatch is mounted removably with respect to the fuselage so as to take up a closed first position in which the hatch closes a lateral opening in the fuselage, and an open second position in which the open hatch allows access to the inside of the tail cone through the corresponding opening The avionic equipment that requires regular inspection and/or maintenance operations is housed in a part of the tail cone which is accessible through the two lateral openings in the fuselage to a person who remains on the outside of the fuselage.

Abstract: Various systems, processes, and techniques may be used for producing a long modular window assembly for an aircraft. In particular implementations, a long modular window assembly may, among other things, include a frame, a motor, and a shade. The frame may include an inner shell and an outer shell. The inner shell may have a lens opening, and the outer shell an opening but no lens. The frame may have a frame interior. A lens may be provided for engagement to the lens opening of the inner shell. A multiplicity of brackets may attach the frame to engage the assembly to a side wall, typically curved, of an aircraft interior. An electric motor may engage the frame in the frame interior along the frame. A first shade is provided with a shade rail. The shade and the shade rail are dimensioned for receipt into the interior of the frame.

Abstract: A windshield (10) of an aircraft (1) of the present invention includes a conductive member (21, 22, 23, 26, 27, 28) that is configured to generate heat when a current is supplied. The conductive member (21, 22, 23, 26, 27, 28) is oriented in a lateral direction (DH) that is a horizontal direction included in an in-plane direction of the windshield (10).

Abstract: An aircraft with a fuselage and a floor structure that is arranged inside the fuselage, the floor structure and the fuselage defining a subfloor region between the floor structure and a fuselage underside of the fuselage, the subfloor region accommodating at least one auxiliary compartment, wherein an equipment bay with at least one auxiliary equipment is arranged within the subfloor region, the at least one auxiliary equipment being at least essentially stowable in the equipment bay in a stow mode and the at least one auxiliary compartment being at least partly arranged in a region between the equipment bay and the floor structure such that the at least one auxiliary compartment separates the equipment bay from the floor structure.

Abstract: The invention discloses an aircraft generating a larger lift from its interior. The fluid channel inside the aircraft communicates with the engine and the ports on the upper surface of the outer shell. With the powerful suction of the engine, the fluid on the upper surface of the outer shell is quickly sucked into the fluid channel via respective ports under conditions of long path, large area, high speed and low air pressure, which results in large lift from the interior of the aircraft. In the course of generating the lift, the fluid resistances of the fluid wall and the fluid hole are sucked into the fluid channel through the ports at the front and the surrounding area of the aircraft, then high-speed fluid is emitted from the rear port. This approach contributes greatly to the transformation of the existing aircraft. The unified big wing significantly improves the lift, the speed and the carrying capacity of the existing aircraft with lowered energy consumption.

Abstract: The present invention is a variable geometry aircraft that is capable of morphing its shape from a symmetric cross-section buoyant craft to an asymmetric lifting body and even to a symmetric zero lift configuration. The basic structure is a semi rigid airship with movable longerons. Movement of the longerons adjusts the camber of the upper and/or lower surfaces to achieve varying shapes of the lifting-body. This transformation changes both the lift and drag characteristics of the craft to alter the flight characteristics. The transformation may be accomplished while the craft is airborne and does not require any ground support equipment.

Abstract: Method and apparatus for controlling a shape of a composite structure. A shape memory structure associated with the composite structure is activated. The shape memory structure changes from a buckled shape to an original shape and causes the composite structure to change from an undeployed shape to a deployed shape. The shape memory structure is deactivated. The shape memory structure changes from the original shape to the buckled shape in response to a load from the composite structure and causes the composite structure to change from the deployed shape to the undeployed shape.

Abstract: A vertical stabilizer for an aircraft, including a fin, pivotable rudder, rudder adjustment arrangement, and vortex generator arrangement having on each side of the fin a turbulence generation element, each turbulence generation element disposed in a surface section of the fin and mounted moveably between a first, retracted position, where it is retracted into an interior space of the fin, and a second, extended position, where it projects at least partially outwardly from the fin transversely with respect to the surface section, and a turbulence generation element adjustment arrangement which is coupled to the rudder. The turbulence generation element adjustment arrangement engages the turbulence generation elements to move them. In a range of angular positions of the rudder, the turbulence generation element adjustment arrangement is inoperative for causing a movement of the turbulence generation elements out of the first position.

Abstract: A flexible flight control system enables conversion from one architecture using one type of inceptor to another architecture using another type of inceptor, through the usage of modular software and hardware pieces with common interfaces among the different types of inceptors. Longitudinal and lateral directional control laws are adapted to be compatible with the specific aspects of the operation of each configuration/architecture, giving the option to the aircraft operator to choose any one of a number of inceptor architectures at time of manufacture.

Abstract: Closed loop control of control surfaces is described herein. One disclosed example method includes measuring a flight metric of an aircraft during flight and calculating, using a processor, a deflection of a control surface of the aircraft based on the flight metric. The disclosed example method also includes adjusting the deflection to an effective deflection level based on the calculated deflection to reduce a drag coefficient of the aircraft.

Abstract: A piloting system having a control stick configured to control the aircraft with respect to its three piloting axes, namely the pitch axis, the roll axis and the yaw axis, and an auxiliary control device configured to automatically control the aircraft during one of the following phases: a landing phase and a takeoff phase. The auxiliary control device automatically controls the aircraft with respect to at least one of the piloting axes, and the other piloting axes, which are not controlled automatically by the auxiliary control device, then being controlled manually by a pilot with the aid of the control stick.

Abstract: Methods and apparatus for reacting rotary actuator and control surface loads into a wing structure using reaction links. The apparatus incorporates a structural interface feature that can facilitate a change of the component(s) in the load loop, such as the path connecting a control surface to a fixed aircraft structure via a rotary actuator. In particular, the structural interface between the rotary actuator and the rear spar of a wing can be tuned for stiffness to achieve an optimized load path that reacts actuator and control surface loads back into the wing structure. An actuator integration objective can be met for any rotary actuator using an integration method which tolerates wing and/or hinge line deflection.

Abstract: An electromechanical hinge-line rotary actuator is provided. The actuator includes a drive member and a motor disposed inside and directly coupled to the drive member. The motor has a rotor configured toward an outside of the motor and directly coupled to an input of the drive member and a stator configured toward an inside of the motor and positioned inside the rotor. The drive member, rotor, and stator are arranged concentrically with each other.

Abstract: A vortex generator arrangement for an aircraft including a surface section, a flap element pivotable between a first position and a second position, a biasing arrangement biasing the flap element towards the second position, retaining devices retaining the flap element in the first or second position, and a release device releasing the flap element from the first retaining device. The biasing arrangement, the first retaining device and the second retaining device are configured such that the second retaining device automatically retains the flap element in the second position after the flap element has been pivoted by the biasing arrangement from the first position into the second position. As soon as the torque exceeds a predetermined value, the second retaining device automatically releases the flap element, which pivots against the force of the biasing arrangement into the first position and is automatically retained therein by the first retaining device.

Abstract: A fuel efficient aircraft propulsion system comprises a wingtip mounted ducted pusher fan with convergent backwash and a skewed conical engine nacelle. The system both mitigates wingtip vortex drag and converts a portion of vortex energy into propulsion force and lift force. The forward-tapering nacelle skews both downward and inward, so the lower nacelle surface is flush with the lower wing surface and the inboard nacelle surface does not alter flow over the upper wing surface. This firstly preserves lift at the outboard wing end. Secondly, air displacement by the nacelle accelerates flow only on the outboard and upper nacelle surfaces, and because the nacelle occupies the core of the nascent wingtip vortex, rotational air velocity is greatest on the upper nacelle surface. The resultant pressure drop on the upper nacelle surface contributes to aircraft lift. And because the nacelle surface tapers forward, this pressure drop does not exert backward-acting drag on the aircraft.

Abstract: A winglet system for an aircraft wing includes an upper winglet and a lower winglet mounted to a wing. The lower winglet has a static position when the wing is subject to an on-ground static loading. The lower winglet may be substantially straight in the static position. The lower winglet is configured such that upward deflection of the wing under an approximate 1-g flight loading causes the lower winglet to move upwardly and outwardly from the static position to an in-flight position resulting in an effective span increase of the wing under the approximate 1-g flight loading relative to the span of the wing under the on-ground static loading.

Abstract: An aircraft landing gear wheel includes a main body with a hub portion and a driven gear portion. The hub portion includes a gear end and an attachment end. The driven gear portion integrally and drivingly connects with the hub portion at the gear end.

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that includes a frame that provides both structural support for the UAV and protection for foreign objects that may come into contact with the UAV. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV may also include one or more pushing motor and propeller assemblies that are oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, the pushing motor(s) may be engaged and the pushing propeller(s) will aid in the horizontal propulsion of the UAV.

Abstract: A rotorcraft includes a proprotor coupled to the wing and a pusher propeller. Power is transferred from the proprotor to the pusher propeller with the use of a torque splitter. The torque splitter contains several gears, including a ring gear which rotates on an axis. The power outputted by the torque splitter is increased or decreased by selectively slowing down the rotation of the ring gear by the use of a clamp.

Abstract: An engine system with a multi-gas-generator, tip-turbine driven lift fan with pressurized air circulation control for use on vertical and short-take-off and landing (V/STOL) aircraft is disclosed. Gas generators located around the periphery of the fan drive the fan through action on a fan blade-tip turbine or provide compressed gas (hot or cold) to circulation control devices. Variable pitch fan blades improve part-power cruise performance. Enclosed in a nacelle, the engine employs circulation control to enhance V/STOL performance. In some embodiments, a core cruise turbine gas generator mounted in the center of the fan duct powers the fan during cruise mode. In some hybrid gas and electric power embodiments, the core cruise gas generator is replaced by an electric motor that draws power from a battery in the fuselage. The battery may be charged by an electric generator driven by a gas generator around the periphery of the fan.

Abstract: FIG. 1 shows an efficient flight path for airframe 10 with camera 16 flying along a transmission line utility corridor containing towers 40, 42, and 44. Between the towers the airframe is in a fast linear glide 18 to check the right of way for encroachment. Abreast of tower 42, the airframe spirals down 20 with power plant 11 off to take more detailed pictures. When the tower inspection is complete, power plant 11 is turned on to start a power climb 22 back up to prepare for glide 24 to the next tower 44, where the airframe again spirals down 26 for a closer inspection. On the return flight, a close-in conductor inspection is flown in catenary arcs with glides 28, 32 on the downslope and power climb 30, 34 on the upslope.

Abstract: Unmanned aerial vehicles and methods for providing the same are disclosed. The unmanned aerial vehicles may have various configurations related to a support frame. The unmanned aerial vehicles may have various configurations with a continuous track for ground propulsion. The unmanned aerial vehicles may have various configurations related to payload clamps.

Abstract: The system includes a snorkel leading from an intake up to a tank borne by an aircraft. A feed pump in the intake draws water up the snorkel to the tank. A polymer gel emulsion reservoir supplies polymer gel upstream of the feed pump for addition and activation of the polymer gel emulsion with the water. A separate pump within the tank provides for selectable recirculation within the tank and/or discharge out of the tank, such as out of a nozzle. Polymer gel emulsion can optionally be supplied at the tank pump rather than the feed pump for delayed addition of polymer gel emulsion to water carried by the aircraft.

Abstract: A pod system for an aircraft is disclosed. Embodiments provide an external, near belly-tangent modular plug-and-play pod system that includes a scalable set of left-side bays which are connected to a scalable set of right-side bays via a central compartment positioned on a bottom external surface of the aircraft's fuselage. The bays accommodate removable slide trays which have various equipment (for example, communications, intelligence, surveillance, and reconnaissance equipment) mounted thereon. The bays and slide trays combination allow for quick removal, insertion, and connection of the various mounted equipment to IP-based connectivity, power, and foundation signals from the aircraft. In an embodiment, the left-side bays, right-side bays, and central compartment each have a planar bottom surface which are substantially equiplanar so that inserted and connected mounted equipment extending downward and externally from the bays from the planar bottom surface have 360 degree unobstructed views.

Abstract: An improved overhead storage system for use in an aircraft may include a variable opening overhead storage bin that is configured to automatically open to an initial open position when a latch mechanism is released and to open further to a second open position when a force is applied to the bin. Such improved overhead storage systems and variable opening overhead storage bins may improve article retention of articles or loads stored within the storage bins during flight. For example, when in the initial open position, the variable opening overhead storage bin may be angled to decrease chances of stowed articles falling out of the bin. When the variable opening overhead storage bin is further opened to the second open position, such as by pressing down on the bin, the passenger's hands may be in a better position to control articles stowed within the bin.

Abstract: A galley cart system employs a housing with a door coupled to the housing, the door configured to be moved between a closed position and an open position. A vent plate in the housing communicates between a first compartment and a second compartment. A valve plate adjacent the vent plate is movable from a venting position when the door is in the closed position to a blocking position when the door is in the open position thereby preventing flow communication between the first and second compartment.

Abstract: Systems and methods are disclosed herein for an aircraft seat with a dual-function linear actuator. The linear actuator may activate a first adjustable feature by moving in a first direction, and the linear actuator may activate a second adjustable feature by moving in a second direction. The linear actuator may include a decoupling mechanism. The decoupling mechanism may decouple the first adjustable feature and the second adjustable feature from the linear actuator in response to loss of power to the linear actuator.

Abstract: A system and method for regulating pressure inside a vehicle (“cabin pressure”) with reduced noise is disclosed. The system can include a forward gate and an aft gate that can be moved from a closed position to an open position to release cabin pressure in a controlled manner. The forward gate and the aft gate can comprise one or more flow disruptors. A first portion of the flow disruptors can be fixed and a second portion can be moveable between a retracted position and a deployed in position. In the retracted position the one or more flow disruptors can reduce broadband noise through the system by smoothing air flow therethrough. In the second position, the one or more flow disruptors can create boundary layer turbulence. The boundary layer turbulence can prevent, or delay, flow separation reducing tonal noises therethrough. In this manner, flow efficiency can be increased and noise reduced.

Abstract: A system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers. The compressing device is bypassed based on the preparing in parallel the medium for the chamber, which in turn enables the compressing device to windmill. Therefore, the system employs at least one mechanism to prevent components of the compressing device from windmilling.

Abstract: A system, which includes a plurality of heat exchangers and a compressing device, is configured to prepare in parallel a medium bled from a low-pressure location of an engine and flowing through a plurality of heat exchangers into a chamber. The compressing device is in communication with the plurality of heat exchangers and regulates a pressure of the medium flowing through the plurality of heat exchangers.

Abstract: A gas turbine engine is provided having a nose cone, wherein the nose cone is symmetrically disposed about an axis. The nose cone includes a leading edge and a base. A forward section is disposed between the leading edge and the base and has a radius at any axial location defined by a first equation. A transition section is disposed between the forward section and the base and has a radius at any axial location defined by a second equation. The first equation is different than the second equation.