Abstract: A cleat attachable device for attaching to a cleat having horns. The device includes a frame having a base end, a distal end opposite the base end, and lateral posts. The lateral posts are disposed opposite one another and are connected to one another at the distal end. The lateral posts each have a respective mounting plate with a longitudinal slot formed therein. A stud plate has an underside for resting on the cleat. The stud plate has two studs opposite the underside for receiving the mounting plates thereon and securing the frame to the cleat.

Abstract: Examples are disclosed that relate to watercraft with retractable drive mechanisms. One example provides a watercraft including a hull having a receiving compartment, and also having a deck. The watercraft also includes a drive unit extending through the deck and the hull of the watercraft and being configured to receive rotational input. The drive unit includes a driveshaft and propeller moveable between an extended position in which the propeller is positioned underneath the hull and a retracted position in which the propeller is positioned at least partially within the receiving compartment.

Abstract: A sport harness for use with a kite or other propulsive device having a quick release feature whereby the user may release himself or herself from the harness while being pulled by a kite. The quick release feature including an interconnection between a spreader bar and one part of a two part waist band closure whereby releasing one end of the spreader bar causes the closure to separate. A harness having vent openings. An overlay for impeding tangling of lines with a harness.

Abstract: A trolling system for a boat includes a trolling motor and a control mechanism. The control mechanism includes an interface for establishing a network connection between the control mechanism and an electronic GPS mapping computer. The control mechanism is configured to receive control instruction from the electronic GPS mapping computer to cause the trolling motor to execute a direction in accordance with a water depth.

Abstract: A blu water lift system for personal watercraft docking systems to raise and lower a personal watercraft into water and retain the personal watercraft for transport. The blu water lift system may be removably attached to boat and a remote activator can be used to manipulate a watercraft between an in-transport condition and a non-transport condition. The blu water lift system may include a carriage structure with a hull-resting plate, at least one carriage rail and at least one pivot mounting arm with at least one bracket assembly, attachment means, and electrically-operated actuator. The blu water lift assembly may be used to removably attach a frame and a carriage structure to a watercraft, operating the at least one pivot mounting arm and operating a loading ramp. Blu water lift systems may be made of corrosion-resistant materials to promote longevity in water-environments.

Abstract: The present disclosure relates to a docking station whereby an underwater robot can be maintained, repaired and managed all the time. According to one aspect of the present disclosure, a docking station can be provided that may comprise: a receiving unit configured to receive an underwater robot therein and positioned under a surface of water; a maintenance unit provided on the receiving unit and positioned above the surface of the water; and a conveyor unit configured to convey the underwater robot from the receiving unit to the maintenance unit.

Abstract: An outdrive for a marine vessel, such as a watercraft having an inboard engine, is provided. The outdrive can include an upper drive unit having a driveshaft that rotates in response to rotation of an input shaft coupled to an engine within a hull of the watercraft. The upper drive unit is movably joined with a lower drive unit, which includes a propeller shaft that rotates in response to rotation of the driveshaft, and an associated propeller. The lower drive unit is movable from a raised mode, in which it is adjacent the upper drive unit, to a lowered mode, in which it is a preselected distance from the upper drive unit, thereby lowering a thrust point produced by the propeller, all while the watercraft is moving through water and while the propeller is producing thrust. A related method and outdrive upper unit are also provided.

Abstract: A watercraft propulsion system is disclosed for an amphibious vessels. The watercraft propulsion system includes a waterjet on each side of the vessel which consist mainly of an impeller, inlet assembly, and stator assembly. The waterjets resists vibrational fatigue and failure through specialized welding between the struts and the inside of the conduit of the inlet assembly. The waterjets can be retrofitted to existing drive shafts to meet the performance requirements of differing amphibious and other marine vessels and to accommodate space limitations. The waterjets are easily installed and removed.

Abstract: A trolling motor system for a light-weight watercraft comprises: a mounting system attaches to the watercraft, the mounting system includes a bracket and a plate, the plate includes a first end, a moveable end, and a hinge therebetween, a connector removably joins the bracket to the watercraft, a pivot connects the bracket to the first end of the plate; a winch is located adjacent the first end and is adapted to raise and lower the movable end between an up position and a down position; a guidance mechanism is coupled to and below the moveable end, the guidance mechanism includes a wire system for controlling rotational movement of the trolling motor; and a trolling motor affixed to and located below the guidance mechanism.

Abstract: An exhaust manifold is for an internal combustion engine on an outboard marine engine that is configured to power a propulsor to provide a thrust in a longitudinal direction. The exhaust manifold comprises an exhaust runner that transversely and longitudinally rearwardly conveys the exhaust gas from the internal combustion engine, an exhaust log that vertically upwardly conveys the exhaust gas from the exhaust runner, and an exhaust elbow that conveys the exhaust gas from the exhaust log vertically upwardly, longitudinally forwardly, and then vertically downwardly.

Abstract: A method of and an arrangement for improving the lubrication system of a propulsion device of a marine vessel are specifically applicable in removing water from the lubrication oil of various types of thrusters. An inert gas is arranged from an inert gas source to flow through a gas cavity in the lubrication system for flushing moist gas from the cavity.

Abstract: A rudder for as ship is described, comprising a rudder blade (10) which is fastened via a rudder stock (32) to the aft end (16) of the ship, where the rudder blade (10) is a rudder blade of the suspension type, comprising a first rudder blade part (12) and a second rudder blade part (14), arranged above and below each other, respectively, the rudder stock (32) is mounted and fastened to the rudder blade (10) and extends up into the aft end (16) of the ship, where the rudder stock is coupled at the upper end to a steering gear (20) arranged at the aft end (16) of the ship. An outer tube (34) is arranged about the rudder stock (32) where the outer tube (34) is fastened in the first, upper rudder blade part (12) and the aft end (16) of the ship, respectively, and that the rudder stock (32) extends through the outer tube (34) and down into the second, lower rudder blade part (14).

Abstract: A bearing element is provided which has at least three individual annular segments which are each combined to form a homogeneous, inherently fixed bearing element. The individual annular segments each abut against at least two further annular segments and are interconnected by connecting means.

Abstract: A system for interconnecting components in a vehicle body structure, and especially for interconnecting fiber-reinforced composite components in a fuselage structure of an aircraft. The system includes a first adapter member, a second adapter member and a connector member. The first adapter member has a first mating portion configured to substantially conform with a profile of a first component of the structure in more than one plane. A first attachment portion is connected to the first mating portion. The second adapter member has a second mating portion configured to substantially conform with a profile of a second component of the structure in more than one plane. A second attachment portion is connected to the second mating portion. The connector member securely interconnects the first and second attachment portions of the first and second adapter members. A related method of interconnecting components in a vehicle body structure is also disclosed.

Abstract: A support system for a crown area of an aircraft and a corresponding method is disclosed. The support system includes a crown integration panel (CIP). The CIP is configured to provide a mounting surface for a plurality of aircraft equipment and to provide an electrical ground for at least one of the aircraft equipment of the plurality of aircraft equipment. The system further includes a first attachment and a second attachment attached to the CIP. The first attachment and the second attachment are configured to attach to an airframe of the aircraft. The system further includes a crown raceway support (CRS) having a first end and a second end, where the first end is attached to a first end of the CIP and the second end is configured to attach to an outboard rail of the aircraft.

Abstract: Aspects of the disclosure are directed to a system configured for installing or removing a door from an aircraft, the system comprising: a pin, a hinge comprising a slot that forms a cavity for rotatively coupling the hinge and the pin, a clamp coupled to the pin, and a retaining mechanism on the clamp that selectively bears against the hinge to maintain the pin in the cavity when the retaining mechanism is engaged and releases the hinge when the retaining mechanism is disengaged.

Abstract: A thermal insulation system for an aircraft that includes leading surfaces is provided. The thermal insulation system includes a carrier and a container. The carrier has an interior surface that includes a first plurality of magnets that generate a first magnetic field, and an exterior surface that is thermally coupled to the leading surfaces of the aircraft. The container is surrounded by the interior surface of the carrier, has an exterior surface including a second plurality of magnets that generate a second magnetic field oriented opposite the first magnetic field, and has an interior that includes electronics. The first magnetic field and the second magnetic field generate a gap between the carrier and the container to reduce a heat transfer from the leading surfaces to the electronics during operation of the aircraft.

Abstract: A system that improves on known systems for reducing output torque by a motor in the event of a jam may include an electromechanical actuator (EMA), a motor configured to drive the EMA and a controller. The controller may be coupled to the motor and configured to receive a speed of the EMA and a position of the EMA. The controller may be further configured to determine whether a jam of the EMA is imminent or is occurring according to the EMA speed, EMA position, and a known range of motion of the EMA, and to provide an input signal to the motor to reduce a torque of the motor if a jam of the EMA is imminent or is occurring.

Abstract: A fairing has a molded body and an electrical wire embedded therein. The body may be constructed from a molded plastics material or a composite material.

Abstract: An accessory gearbox for a turboshaft engine of an aircraft, the gearbox including a casing, an aircraft wing flap control rod arranged so as to slide axially inside the gearbox and an actuator for driving the control rod which is mounted on the casing, the actuator including a hollow body, a piston which is arranged so as to move in translation inside the body and a piston rod which is connected to the piston and extends at least in part outside the body of the actuator the piston rod being connected to the control rod, wherein the actuator is arranged between the connection of the piston rod and the control rod, and the casing of the gearbox.

Abstract: A geodetic measuring system having a geodetic measuring unit having a beam source for emitting a substantially collimated optical beam. The measuring system also has an automotive, unmanned, controllable air vehicle having an optical module. An evaluation unit is also provided, wherein the evaluation unit is configured in such a manner that an actual state of the air vehicle, as determined by a position, an orientation and/or a change in position, can be determined in a coordinate system from interaction between the optical beam and the optical module. The measuring system has a control unit for controlling the air vehicle, wherein the control unit is configured in such a manner that control data can be produced using an algorithm on the basis of the actual state, which can be continuously determined in particular, and a defined desired state, and the air vehicle can be automatically changed to the desired state.

Abstract: A system for controlling aircraft boundary layer airflow comprising a frame structure configured to be coupled or integral to an inner surface of an aircraft nacelle, the frame configured to support to the nacelle, and/or a modular plenum configured to be received by the frame structure, the modular plenum comprising a truncated tetrahedron intersected at its apex by a duct. The frame may comprise a plurality of sub-frames. The system may further comprise a plurality of modular plenums, each configured to fit within a sub-frame. The system may further comprise a flexible material configured to couple a first duct to a second duct. The system may further comprise a nacelle configured to receive the system.

Abstract: A steering valve includes a housing and a spool disposed inside the housing. The housing includes a top plane and a bottom plane, the top plane including an opening of a first port and the bottom plane including an opening of a second port. The spool includes a top plane including a first and second opening corresponding to a third port and a fourth port, one of which is configured to align with the opening of the first port depending on the orientation of the housing. The spool also includes a bottom plane including a first and second opening corresponding to the third port and fourth port, one of which is configured to align with the opening of the second port depending on the orientation of the housing.

Abstract: Lift offset management and control systems are provided for a rotorcraft including main rotor and auxiliary propulsor assemblies, the main rotor assembly including first and second rotors disposed to oppositely rotate relative to an airframe about a same rotational axis, and sensors disposed to generate hub moment, tip clearance and lift offset data of the main rotor assembly.

Abstract: One embodiment of a method of calculating appropriate helicopter rotor adjustments, a method of calculating helicopter rotor adjustment coefficients, a method of producing a set of rotor adjustment coefficients for a specific rotor based on a limited data set, a software application for rotor balance, and a computing system for rotor balance.

Abstract: A helicopter autopilot system includes an inner loop for attitude hold for the flight of the helicopter including a given level of redundancy applied to the inner loop. An outer loop is configured for providing a navigation function with respect to the flight of the helicopter including a different level of redundancy than the inner loop. An actuator provides a braking force on a linkage that serves to stabilize the flight of the helicopter during a power failure. The actuator is electromechanical and receives electrical drive signals to provide automatic flight control of the helicopter without requiring a hydraulic assistance system in the helicopter. The autopilot can operate the helicopter in a failed mode of the hydraulic assistance system. A number of flight modes are described with associated sensor inputs including rate based and true attitude modes.

Abstract: A rotor drive for a tail rotor of a helicopter is provided. The system includes a stator and a rotor mounted to the stator with a rotatable central carrier. Rotor blades are radially attached to the rotatable central carrier and each of the rotor blades is pivotable about their respective radial central axis for variation of blade pitch. At least one permanent magnet is provided on each rotor blade. A plurality of electromagnets is provided on the stator close enough to allow inductive interaction between the plurality of electromagnets and the at least one permanent magnet on each rotor blade. The permanent magnets are offset from the radial central axis in a direction perpendicular to the rotation plane for individual pitch control of the rotor blades by individual control of electric supply to the electromagnets.

Abstract: A first pattern associated with a performer may be recognized based upon visual information. A sensor carried by an unmanned aerial vehicle may be configured to generate output signals conveying the visual information. A first distance may be determined between the first pattern and the unmanned aerial vehicle. A second pattern associated with a performee may be recognized based upon the visual information. A second distance may be determined between the second pattern and the unmanned aerial vehicle. Flight control may be adjusted based upon the first distance and the second distance. A flight control subsystem may be configured to provide the flight control for the unmanned aerial vehicle.

Abstract: An aircraft is provided and includes a mission vehicle configured to follow vertical take-off and landing (VTOL) operations and to execute forward flight, hover/loiter and landing operations and a launch vehicle configured to drive the mission vehicle through at least vertical take-off (VTO) operations. The launch vehicle is umbilically coupled to the mission vehicle during the VTO operations and releasable from the mission vehicle thereafter.

Abstract: Described are portable electronics device coupling assemblies including a cradle configured to electronically couple and releasably engage a portable electronics device, and an adaptor configured to electronically couple and releasably engage the cradle to a passenger seat. Other examples may include a passenger seat having an electronics port configured to electronically couple to the portable electronics device, and a receptacle coupled to the electronics port and configured to releasably engage the portable electronics device. As examples, the portable electronics device may be a tablet computer, a cell phone, a smart phone, a handheld video game system, a personal digital assistant, a palmtop computer, a DVD player, data or audio-video media, or a multi-media enabled device.

Abstract: A support structure for attachment to a tray table for a passenger seat, a tray table for a passenger seat, and a passenger seat. The support structure comprises a support arm shaped to substantially match at least a first portion of a peripheral contour of the tray table; and a connecting structure for connecting the support arm to the tray table in a manner such that the support arm is configurable into a stowed position in which the support arm extends substantially along said at least first portion of the peripheral contour of the tray table and at least one support position for supporting an item on the tray table in an angled orientation between a surface of the item and the surface of the tray table.

Abstract: An aircraft passenger seat having a seat bottom, a seat back, and right and left armrests. The arm rests include structural arm rest assemblies for attachment to the seat bottom, and arm rests for being removably-positioned on the structural arm rest panels. Upholstery shrouds are adapted for being positioned on and covering the right and left arm rests. The shrouds are easily removed and installed as needed.

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: A method for reducing a turbine clearance gap between a plurality of rotor blades of a turbine engine and a shroud of the turbine engine is provided. The method includes determining that an airplane is in a first flight condition, and adjusting the turbine clearance gap to a first clearance gap distance associated with the first flight condition. The method also includes determining a demand for a second flight condition, and adjusting an engine responsiveness to a first engine responsiveness for a first predetermined change in a power parameter of the engine. The method further includes reducing the engine responsiveness from the first engine responsiveness level to a second engine responsiveness level for a second predetermined change in the power parameter of the engine, and closing a clearance control valve associated with the shroud during the second predetermined change in the power parameter of the engine.

Abstract: A swept gradient air boundary layer diverter for an aircraft. The aircraft includes a fuselage and an air inlet for an engine of the aircraft, where the air inlet includes a cowl at a leading edge of the inlet. The diverter includes a V-shaped ramp portion formed in the fuselage in an area proximate to and in front of the cowl where the ramp portion extends downward away from an outer surface of the fuselage towards an inside of the aircraft. The diverter also includes a V-shaped trough portion formed into the fuselage and being positioned adjacent to and integral with the ramp portion between the ramp portion and the air inlet. Air flowing over the fuselage towards the cowl is expanded and compressed by the ramp portion and the trough portion so as to create pressure gradients that generate vortices to redirect boundary layer airflow around the air inlet.

Abstract: A jet noise suppressor including a nozzle having a front end and an opposed rear end, spokes extending radially inward from the nozzle, the spokes defining vents, and a center-body connected to the spokes and in fluid communication with the vents, the center-body being positioned centrally within the nozzle and including a closed front end and an open rear end, wherein the front end of the nozzle entrains a first ambient airflow passing through the nozzle and exiting the rear end of the nozzle proximate a periphery of the nozzle, and wherein the vents entrain a second ambient airflow passing through the center-body and exiting the rear end of the nozzle proximate a center of the nozzle.

Abstract: Commercial aircraft fuel tanks, such as the center wing tank or body tanks, can be subject to explosion hazard due to heat balance around the tanks. Various embodiments of the present disclosure reduce the flammability exposure of the fuel tank by drawing cold air from a cold air unit of the aircraft and passing the air to a space proximate the fuel tank, without disrupting the cold air system in flight performance.

Abstract: A small thin display unit that can be installed in the flight deck for displaying only flight crew-selected tactical information needed for the task at hand. The flight crew can select the tactical information to be displayed by means of any conventional user interface. Whenever the flight crew selects tactical information for display, the user interface sends a corresponding request for tactical information to a computer system. The computer system processes the request, including periodically retrieving measured current values or computing current values for the requested tactical parameters and returning those current tactical parameter values to the display unit for display.

Abstract: Embodiments of air flow sensing systems are provided herein. In some embodiments, one or more sensors are positionable on an aircraft and dimensioned and arranged to measure vector components of airflow velocity having at least one of a transverse or streamwise direction relative to a flight direction of the aircraft. In some embodiments, the one or more sensors are positioned in front of an aircraft wing and distributed as an array of sensors along the span of the aircraft wing.

Abstract: A blade tracking system for a rotary wing aircraft includes a blade sensor mounted on a blade of the rotary wing aircraft, the blade sensor wirelessly transmitting blade data; a reference sensor mounted to the rotary wing aircraft, the blade driven by the rotor hub, the reference sensor transmitting reference data; and a processor receiving the blade data and the reference data, the processor determining at least one of lead-lag, flap and pitch of the blade in response to the blade data and the reference data.

Abstract: An exterior aircraft light unit for emitting light of a first wavelength and light of a second wavelength, different from the first wavelength, with corresponding emission characteristics is disclosed. The exterior aircraft light unit has at least one first light source configured to emit the light of the first wavelength, at least one second light source configured to emit the light of the second wavelength, and a wavelength selective optical element, which wavelength selective optical element is reflective for the light of the first wavelength and transparent for the light of the second wavelength.

Abstract: Micro satellite is disclosed with foldable solar panels that may be winded around the body of the micro satellite so that the growth in outer dimensions of the satellite is no more than 10-20 mm along each one of the length, width and height of the microsatellite so that the micro satellite may be launched in an auxiliary payload volume of a launcher. The foldable solar panels may be deployed to employ area that exceeds 9 times the product of the length by the width of the satellite and 6 times the product of the height by the length. The solar power produced by the solar panel and their light weight enable carrying of cargo that is at least 0.6 of the of the total mass of the satellites.

Abstract: A method of manufacturing a solar cell assembly by providing a substrate; depositing on the substrate a sequence of layers of semiconductor material forming a solar cell; mounting a permanent laminate supporting member with a thickness of 50 microns or less on top of the sequence of layers; utilizing the laminate structure for supporting the epitaxial sequence of layers of semiconductor material forming a solar cell during the processes of removing the substrate and depositing and lithographically patterning a plurality of metal grid lines disposed on the top surface of the first solar subcell, and attaching a cover glass over at least the grid lines of the solar cell.

Abstract: A system, method, and apparatus for a vented launch vehicle adaptor (LVA) for a manned spacecraft with a “pusher” launch abort system are disclosed. The disclosed LVA provides a structural interface between a commercial crew vehicle (CCV) crew module/service module (CM/SM) spacecraft and an expendable launch vehicle. The LVA provides structural attachment of the module to the launch vehicle. It also provides a means to control the exhaust plume from a pusher-type launch abort system that is integrated into the module. In case of an on-pad or ascent abort, which requires the module to jettison away from the launch vehicle, the launch abort system exhaust plume must be safely directed away from critical and dangerous portions of the launch vehicle in order to achieve a safe and successful jettison.

Abstract: A space relevator adapted to transition an object between a stationary compartment and a rotating module rotating in a first direction, the relevator comprising: a relevator module comprising a plurality of substantially solid pie-shaped structures separated by a plurality of pie-shaped compartments all positioned around a central axis; a relevator central shaft extending along the central axis; the relevator module being adapted to receive a rotate signal and a stop signal, one or more of the pie-shaped compartments comprising an entry between the stationary compartment and the rotating module when the relevator module receives a stop signal and after the relevator module receives a rotate signal.

Abstract: The invention relates to a filling and closing device (20) for an applicator for active substances (1) and to a method for filling and closing such an applicator for active substances (1) by means of such a filling and closing device (20). The applicator for active substances (1) comprises an applicator tube (7) that overlaps the sealing edge (5), at least in part. The filling and closing device (20) comprises a receiving element (21) for the lower part (2) of the applicator for active substances (1), having a circumferential pressure surface (22) and a receiving channel (23) for the applicator tube (7), said receiving channel extending below the pressure surface (22). The receiving element (21) is constructed of at least two parts, having a base element (24) and a cover element (25) that is movable with respect to the base element (24).

Abstract: A gripping head for a loading robot or manipulator of a cartoning machine capable of nesting articles arranged on two substantially parallel rows, the gripping head comprising a row of gripping members, wherein each of the gripping members comprises a gripping section adapted to receive two adjacent articles and on opposite sides with respect to a centerline plane, and wherein at least the gripping members having even index position or odd index position in the row rotate by about 180 degrees around an axis.

Abstract: A drive assembly (17) to move tubular bag material past a former and deliver a tubular bag material to a packaging machine. The drive assembly (17) includes a pair of drive belts (6) that are parallel and driven in unison by means of a drive pulley (29) and either pulleys (30, 31).

Abstract: A filling apparatus for filling containers, and a method of operation, are disclosed, whereby a plurality of container carriers are movable along an upper container guideway of the apparatus. Notably, a pair of servo drives in the form of linear actuators act generally in opposition to each other, at opposites ends to the container carriers movable along the container guideway, to accurately index and position the container carriers with respect to associated filling equipment. Servo-driven transfer wheels, positioned at respective opposite ends of the upper container guideway, effect movement of the containers to and from a return conveyor positioned beneath the upper container guideway, whereby the container carriers are moved from the downstream end of the filling region back to the upstream end thereof.

Abstract: The invention relates to a method for sterilizing packaging material, comprising an emitter that is adapted to emit charge carriers, in particular electrons, wherein the charge carriers form at least one cloud, and wherein the emitter and the packaging material are moved relative to each other so that a flow of a gaseous medium is established in between the emitter and the packaging material. The method comprises the steps of: controlling a movement profile between the emitter and the packaging material; sterilizing the flow of the medium in between the emitter and the packaging material by adjusting the movement profile so that the flow of the medium in between the emitter and the packaging material is sterilized. Also disclosed is a device for sterilizing packaging material.