Abstract: A trim stabilizer device to be communicated with a transom of a motor boat includes a foil tiltable around its transversal axis and the foil is structurally independent from the transom. An actuator communicates with the foil for tilting. A slide mechanism communicates with the actuator for making a translatory motion thereof relative to the transom. A disc having at least one guide groove guides the slide member; and a connecting member connects the trim stabilizer device to the transom, the connecting member communicates with the disc.

Abstract: A deployable stowable beverage bar system that can be securely but detachably connected to the side of a pleasure craft. The beverage bar having seating on which a swimmer next to the boat can sit and have access to a bar to place a drink or food on when sitting in the seating provided. The beverage bar system can be folded up next to the boat above the water line so the boat can be moved without the beverage bar system causing undue drag on the boat while moving or act as an obstruction to navigation and easily redeployed when the boat stops at a new anchorage.

Abstract: The disclosure provides a semi-submersible offshore platform with columns having an enlarged base on the bottom of each column with pontoons coupled between the columns. The enlarged column base can be at least as high as a height of the pontoon and on at least embodiment can be about 50% of the draft of the platform. The enlarged base can change a current flow shape around the base and columns for lower VIM. An outside corner of the base can be trimmed at an angle. Alternatively, the lower portions of the columns can be extended horizontally outward to form an effectively enlarged base having similar characteristics. In some embodiments, the pontoon volume can be reduced inversely proportional to the base enlargement to have comparable total buoyancy.

Abstract: A fastening device including a first tube defining a first major axis, a distal portion, a proximal portion, and a through hole, the proximal portion of the first tube including an attachment element. A second tube is disposed within the through hole of the first tube, the second tube defining a second major axis that is substantially orthogonal to the first major axis. The attachment means may be one or more notches, a flange, a socket, a wedge and a clamp, or an arm. The first tube may have a bend, and the bend may be between approximately 25° and approximately 30°. Further, the second tube may define a second tube length, and may include a first component and a second component that screw together to provide an adjustable second tube length. The first tube and second tube may be pivotally coupled.

Abstract: Method for mooring an offshore structure includes: providing a mooring line having one end connected to the sea bed and a connector at a free end; lifting the free end onto a deck of an anchor line handling vessel; connecting on the anchor line handling vessel a chain tensioner with a connection side to the connector; providing a working chain having a short tensioning part and a long installation part into the entry side of the chain tensioner; holding a free end of the installation part while lowering the chain tensioner below water level; picking up a free end of a pendant attached to the offshore structure, and attaching it to the free end of the installation part in an interconnect position on the anchor line handling vessel; placing the interconnect position overboard; connecting a lifting cable on the anchor line handling vessel to the tensioning part below water level; and exerting an upward tensioning force on the tensioning chain part.

Abstract: An inflatable launch and recovery system for a towed body is provided. The system is containerized for ease of transport. A container houses a tow body, tow cable, a winch, winch controls, an inflatable ramp, deployment and retrieval equipment, power junctions and air line connections. Inflatable arch shaped tubes and spacer fabric form the ramp structure from which the tow body can be launched and recovered. The ramp can be ballasted to provide hydrodynamic stability and to provide sufficient system depth to accommodate retrieval of towed bodies operating below a liquid medium surface. Additional control can be achieved using inflatable or rigid fin elements or downward lifting surfaces. A rigid clamping fixture connects the ramp structure to the vessel. A snubber element dampens vibrations and transient tow loads.

Abstract: A carrier frame on a vessel for local water motion includes a carrier frame (2); an actuator system (4, 5, 6) adapted for translating the carrier frame (2) along a z-axis and rotating the carrier frame around an x-axis and an y-axis; a sensor system (8) for sensing z-axis translational movement and x-axis and y-axis rotational movements of the vessel; and a control system (9) generating control signals for driving the actuator system in response to the sensor signals. The actuator system includes at least three cylinder-piston-units each having a longitudinal axis (14), which longitudinal axes are mutually parallel in a rest position. Each cylinder-piston unit has an upper support (15) for supporting the carrier frame on said cylinder-piston-unit and a lower support (16) for supporting the cylinder-piston-unit on a base. The upper support and/or lower support allows for rotational movement.

Abstract: A floating installation for temporarily accommodating objects that are being transported from a first position to a second position located on a marine installation, characterized by the floating installation including at least one marine docking station adapted for the call of a seagoing transport vessel, the at least one docking station being integrated in the installation, at least one helipad and living quarters, and a method of transporting personnel and equipment.

Abstract: An arrangement of floating platforms is provided, including (a) an anchored main platform and (b) one or more outer platforms, each of which being connected to the main platform by at least one connection element. One or more of the main and/or outer platforms are rotatable about a vertical axis by drive units which are fixed thereon. Marine engines having a propeller propulsion system are provided as drive units on the main platform and/or the outer platforms.

Abstract: A tactical flotation safety system having a tactical flotation safety vest attachment removably attached to a tactical vest. The tactical flotation safety vest attachment has two side panels adjustably attached at the back and which are secured at the front and back of the tactical vest with cover panels. The two side panels include inner flaps and outer flaps enclosing inflation bladders and inflation mechanisms. The inflation mechanisms are secured to the interiors of the side panels and connected to exterior handles. When necessary, a user may deploy the inflation bladders by pulling on the handles to activate a pressurized gas source, such as liquid carbon dioxide cartridges of the inflation mechanism thereby inflating the bladders to provide buoyancy to the user.

Abstract: The invention concerns a group of vessels (24), having an unmanned surface vessel (3) and an unmanned underwater vessel (1, 1a), wherein the underwater vessel comprises a location device, in particular a sonar device, for sensing location data (12) in the underwater area and one evaluation unit or more evaluation units, and the evaluation unit or the evaluation units are arranged in such a manner that these comprise detection means (20) for detecting (14) a contact (MILEC) with the aid of the sensed location data (12) and with classification means (21) for classifying (15) the detected contact (MILEC) as a mine-like contact (MILCO) or non mine-like contact (NONMILCO), whereby classification is accomplished by comparing the contact (MILEC) with known mine information so that a mine-like contact (MILCO) can be identified as a mine contact (MINE) or as another object (NOMBO).

Abstract: Provided is a floor apparatus which is vertically movable with a thruster canister within a vertical trunk of a hull. The floor apparatus includes a floor frame which is installed in an upper space of a vertical trunk of a ship, that is, a space above a thruster canister. The floor frame is installed to be vertically movable along the vertical trunk. The side of the floor frame is installed to be vertically movable while being guided along the sidewall of the vertical trunk. In particular, at least one pair of guide frames which guide the side of the floor frame are symmetrically installed on the sidewall of the vertical trunk.

Abstract: A propeller shaft assembly having a propeller shaft member defining an inner volume. A foam liner member is disposed in at least a portion of the inner volume of the propeller shaft member. The foam liner member is made of a viscoelastic, natural oil polyol-based foam, whereby the foam liner member is operable to reduce vibration amplitudes occurring within the propeller shaft member relative to an undampened propeller shaft member.

Abstract: There is provided an automatic steering device with which a heading can be stably controlled even under powerful disturbance. The control computer 8 outputs an ordered rudder angle calculated based on the drift angle and the turning angular velocity. The angular velocity inversion timing acquisition component 21 acquires a timing at which the turning angular velocity changes from a direction in which a divergence of the drift angle from zero increases to a direction in which the divergence decreases. The steering stop command component 22 orders a steering stop based on the above-mentioned timing. The steering gear controller 10 controls a steering gear such that it changes a rudder angle of the steering gear based on the ordered rudder angle, and such that it does not change the rudder angle while a command of the steering stop has been received.

Abstract: An apparatus and method for use with a marine vessel having a first steerable propeller and a second steerable propeller is disclosed. The apparatus and method providing for movement of the first and second steerable propellers relative to each other and also maintains a minimum distance between the first and second steerable propellers so as to prevent the first and second steerable from contacting each other. Also disclosed is a control system and method to control the first steerable propeller and the second steerable propeller to provide the fixed distance between the first and second steerable propellers and so as to individually control the first steerable propeller and the second steerable propellers to allow the first steerable propeller and the second steerable propeller to move relative to each other.

Abstract: This disclosure relates to the use of a method for adjusting an altitude of variable-buoyancy vehicle, such as an aerostatic balloon. The method includes determining a target mass for a variable-buoyancy vehicle, where the target mass is based on a target altitude for the variable-buoyancy vehicle. Additionally, the method includes adding a first mass to the variable-buoyancy vehicle. The mass added is less than a difference between the target mass and a current mass. The method also includes adding a second mass to the variable-buoyancy vehicle in response to a decrease in an internal pressure of the variable-buoyancy vehicle caused by adding the first mass. Further, adding the second mass makes a current mass of the variable-buoyancy vehicle approximately equal to the target mass.

Abstract: A frame element (10; 10?) for use in an aircraft component assembly system (46) is attachable to an aircraft structure (36) and comprises at least one fastening device for fastening at least one aircraft interior component (34) or at least one insulation pack (52) to the frame element (10; 10?). An aircraft component assembly system (46) comprises a plurality of such frame elements (10; 10?). In a method of fitting a component (34, 52) in an aircraft, a frame element (10; 10?) is provided. At least one interior component (34) or at least one insulation pack (52) is fastened to the frame element (10; 10?). Then the frame element (10; 10?) having the at least one interior component (34) or the at least one insulation pack (52) fastened thereto is attached to an aircraft structure (36).

Abstract: An impact protection plate is provided for mounting on the structure of an aircraft. The impact protection plate includes a first layer, close to the aircraft, made of a fiber-reinforced plastic having a wave-shaped pattern of alternating elevations and depressions, the transverse tensile strength of the fiber-reinforced plastic being greater than 50 MPa. The impact protection plate includes a second layer situated on the first layer, remote from the aircraft, and is made of a fiber-reinforced plastic, the elongation at break of the reinforcement fibers being greater than 3%.

Abstract: A system and method for installing a window panel onto an aircraft including providing a retaining device having an outside edge that is sealed against an inboard surface of the aircraft. A biasing member mounted to an inside edge of the retaining device includes spring clips that press against the window panel. The spring clips push the window panel outward against the outside edge of the retaining device to maintain a seal around the edge of the window panel.

Abstract: A power drive unit, including a plurality of diagonal rollers arranged at a circumference around a central roller axis and each of the plurality of diagonal rollers having a respective diagonal roller axis, a first drive motor coupled to a roller carrier and configured to rotate the plurality of diagonal rollers around the central roller axis, and a second drive motor coupled to a gear carrier and configured to rotate each of the diagonal rollers around the respective diagonal roller axis. The diagonal roller axes are tilted by a common skew angle with respect to the central roller axis.

Abstract: An airfoil section of a propeller for a propulsion device includes a pressure surface and a suction surface, the pressure surface and suction surface intersecting at a leading edge and a trailing edge. The airfoil section has a meanline defined midway between the pressure surface and the suction surface and a meanline angle is defined as an angle between a tangent to the meanline and a centerline of the propeller. The blade has a meanline curvature defined as the slope of a meanline angle with respect to chord fraction along the meanline, and at least a portion of the meanline has a meanline curvature that increases from between approximately 0.1 chord fraction progressing toward the leading edge and at least a portion of the meanline has a meanline curvature that decreases from between approximately 0.1 chord fraction progressing toward the leading edge.

Abstract: A system and method for a controlling an aircraft with flight control surfaces that are controlled both manually and by a computing device is disclosed. The present invention improves overall flight control operation by reducing the mechanical flight control surface components while providing sufficient back-up control capability in the event of either a mechanical or power-related failure. Through the present invention, natural feedback is provided to the operator from the mechanical flight control surface which operates independent of computer-aided flight control surfaces. Further, through the present invention, force input signals received from the pilot are filtered to improve the operation of the computer-aided flight control surfaces.

Abstract: One example of an aircraft fuel transfer chamber includes a chamber housing including a first sub-chamber defining a first inlet to be connected to an outer tube of a first aircraft fuel line assembly. The first sub-chamber receives fuel leaked into the outer tube of the first aircraft fuel line assembly from an inner tube of the first aircraft fuel line assembly. The chamber housing also includes a second sub-chamber connected to the first sub-chamber, the second sub-chamber defining a second inlet to be connected to an outer tube of a second aircraft fuel line assembly. The second sub-chamber receives fuel leaked into the outer tube of the second aircraft fuel line assembly from an inner tube of the second aircraft fuel line assembly. The chamber housing defines an outlet connected to the first inlet and the second inlet to transfer leaked fuel toward a drain of the aircraft.

Abstract: A method and apparatus to control movement of a vehicle using a plurality of thrust-producing devices formed in at least one control surface is disclosed. A supply of power to the plurality of thrust-producing devices that are configured to propel gas through the control surface to produce thrust is controlled such that a physical displacement of the control surface is generated. The physical displacement is in accordance with the supply of power to the plurality of thrust-producing devices and controls the movement of the vehicle.

Abstract: A vortex generator may include a depression in an aerodynamic surface, and a vortex generator leading edge located in the depression. The vortex generator leading edge may include a leading edge upper surface. The leading edge upper surface may be positioned at or below a tangent line defined at a location along the aerodynamic surface upstream of the depression relative to an oncoming local flow.

Abstract: A method and system for maintaining visual vertical reference on a rotorcraft display during rotorcraft landing is provided. The method generates vertical poles and positions them on the rotorcraft display such that vertical reference as well as roll information may be quickly and easily comprehended by a pilot.

Abstract: Methods, systems, and apparatus, including computer programs encoded on computer storage media, for a distributed system architecture for unmanned air vehicles. One of the methods includes receiving selections of configuration information to provide to an unmanned aerial vehicle (UAV), with the selections of configuration information being associated with respective components included in the UAV. The configuration information associated with a first component is determined to be valid from selections of configuration information associated with the first component. The configuration information associated with the first component is provided for storage in the UAV in response to receiving a user action.

Abstract: The bottom surface of an aircraft, such as an Osprey V-22 propeller driven aircraft, has at least four distributed hook attachment points. A load suspension apparatus is attached to the four attachment points with elongated slings. The load suspension apparatus includes an upper rigid frame and a lower rigid frame of lesser dimensions. The lower frame is suspended from the upper frame with V-shaped slings. A cargo load is attached to the lower frame. The load suspension apparatus provides stable attachment of loads to tilt wing and rotary wing aircraft at high aircraft speeds, at transitions between high and low speeds and through aircraft turns.

Abstract: A suspension system (10) of an aircraft (1). The suspension system (10) comprises a fastener device (15) including a coupling member (20) suitable for carrying a load (5) with a sling (21). The suspension system (10) has a return device (30) that comprises a linkage (40) provided with a plurality of bars (41, 42, 43) hinged in pairs to apply a non-linear force to the coupling device (15), said linkage (40) being suitable for fastening to a load-carrier structure (2) of an aircraft (1). In addition, the return device (30) includes a tie (35) connecting said linkage (40) to the coupling device (15), as well as a spring member (36) fastened to a bar (41) of the linkage (40) and suitable for being connected to an aircraft (1).

Abstract: An automated transport device for moving a cargo unit within an aircraft cargo compartment is provided. The transport device comprises a base body and shifting means, wherein the base body is to carry the cargo unit. The shifting means is to generate a movement of the base body along a floor of the cargo compartment perpendicular to the longitudinal axis of the aircraft and, after that, along the longitudinal axis of the aircraft without rotation of the base body.

Abstract: A passenger service system includes an individual ventilation arrangement and/or a lighting arrangement, wherein at least one air nozzle of the individual ventilation arrangement and/or at least one reading lamp of the lighting arrangement is/are disposed in the region of a service surface of the passenger service system. The service surface of the passenger service system includes a substantially flat portion as well as a buckled portion, which is curved convexly relative to the substantially flat portion and extends along a longitudinal axis (LP) of the passenger service system.

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: Provided is an aircraft lavatory unit that advantageously allows for a reduced number of parts, simplified assembly, and reduced costs while ensuring convenience. First and second lavatories are provided adjacent to one another within a structural frame. Respective sinks of the lavatories are disposed by being attached to the partition wall. A trash insertion port is provided on a wall surface of each base. A single storage chamber provided within the bases of the sinks of the lavatories extends into the bases of the sinks of the lavatories through an opening provided in the partition wall. A trash can device has a single trash can housed in the storage chamber and a single fire extinguisher. A water heater is singularly provided, which is disposed within the base of one of the sinks.

Abstract: An integrated aircraft galley structure includes a service module having a plurality of galley inserts including at least one oven and at least one refrigeration unit. The service module is formed with a plurality of bays sized to receive the plurality of galley inserts, along with a human machine interface for controlling all of the galley inserts. The service module further includes a plurality of galley insert modules for controlling each galley insert, and an insert power and control unit for each galley insert for controlling power to said insert. The entire system is controlled by a galley power and control unit for controlling each of the insert galley power and control units, and an AC distribution unit for distributing power to the insert power and control units.

Abstract: The invention is a seal assembly, including a polyvinyl fluoride (PVF) film bonded to a polyvinylidene fluoride (PVDF) substrate and attached to a plastic retainer element for being mounted to an aircraft passenger fixture by mounting holes formed in the retainer element through which fasteners extend into the seat. The seal is sufficiently flexible to bend into an inner sidewall of an aircraft cabin and to seal a space between the aircraft cabin fixture and the inner sidewall.

Abstract: A carry-on passenger seat adapted to mount upon a support pedestal in an aircraft, the seat including a seatback pivotably connected to a seat bottom such that the seatback is configured to fold against the seat bottom, and an elongate slot formed in an underside of the seat bottom, an elongate member of the support pedestal adapted to be received through the elongate slot and rotated relative thereto to prevent the seat bottom from being pulled apart from the support pedestal.

Abstract: There is provided an aircraft folding seat, comprising a frame which pivots about a vertical axis and on which are mounted a seat-rest and a back-rest. The flight deck provided comprises control and/or viewing devices, at least one seat, an access door and a corridor for access to the at least one seat which is closed at its opposite end to the at least one seat by the access door. A folding seat is mounted in the corridor such that it can pivot and adopt a first position in which it closes the corridor so forming a lock enclosure with the access door and a folded back second position enabling access to the at least one seat from the corridor.

Abstract: A system and method for exiting a crew rest area located in an overhead area in an aircraft. An opening in the crew rest area is located in an overhead area in the aircraft. An egress apparatus is configured to move between a closed state and an open state. The egress apparatus is configured to direct a person moving on the egress apparatus from the opening to a passenger cabin in the aircraft when the egress apparatus is in the open state.

Abstract: An example inlet duct screen assembly includes a grid portion including a plurality of apertures and a frame portion circumscribing the grid portion. The grid portion and the frame portion are formed from a single sheet of material.

Abstract: An aircraft fuel storage device having at least one main reservoir designed to contain a first batch of fuel and at least one feed line for supplying a propulsion engine of the aircraft with the first batch of fuel contained in the main reservoir and having at least one auxiliary reservoir, designed to contain a second batch of fuel separate from the first batch of fuel, and wherein the auxiliary reservoir is connected to the main reservoir. The device also having an intake line for bringing the second batch of fuel contained in the auxiliary reservoir toward a combustion chamber of the aircraft independent of the propulsion engine of the aircraft.

Abstract: A gas separation method includes flowing a gas feed along a feed flow path within a housing directionally from a product end to a feed end of a gas separation membrane. After the feed flow path, the gas feed flows along a membrane flow path defined by the membrane from the feed end to the product end. The feed flow path is counter to the membrane flow path. Heat may be exchanged between the feed flow path and the membrane flow path and increase separation efficiency. Also, heat exchanged may compensate for some temperature drop in the membrane due to enthalpy of gas separation. A gas separation module includes a feed flow path within a housing extending directionally from a product end to a feed end of a membrane. The feed flow path is counter to a membrane flow path defined by the membrane.

Abstract: A system ensures the correct type of fuel is dispensed in an aircraft while removing the introduction of human error in the refueling process. The system includes an RFID tag disposed at one or more aircraft that electronically stores data such as engine type, engine hours, fuel type, tail number, and pilot/subscriber data for the aircraft on which the RFID tag is disposed. An RFID reader is disposed at or near a fuel dispensing mechanism, such as a fuel truck or tank. A signal indicative of fuel type is emitted from the RFID tag to the RFID reader. RFID tags on aircraft that are enrolled in the system's subscription service enable aircraft to be recognized by a module operating the fuel dispensing mechanism. Based on a comparison performed by the module, authorization to begin fueling is either permitted or declined.

Abstract: Electric aircraft, including in-flight rechargeable electric aircraft, and methods of operating electric aircraft, including methods for recharging electric aircraft in-flight, through the use of an unmanned aerial vehicle (UAV) flying independent of and in proximity to the electric aircraft. The electric aircraft and methods of operating and recharging same may involve establishing, in-flight, an electrical connection between the aircraft and the UAV flying in proximity to the aircraft and transferring electricity from an electricity source associated with the UAV to the aircraft through the electrical connection.

Abstract: Systems and methods for reducing the number of runway excursions (i.e., airplanes going off the end of a runway). An alerting system is provided which alerts pilots when computer calculations indicate that current airplane braking is insufficient to keep the airplane from going off the end of the runway. The current airplane braking during rollout is evaluated using algorithms which take into account the current groundspeed of the airplane, the current deceleration rate or the maximum manual deceleration rate of the airplane, and the distance from the current position of the airplane to the end of the runway.

Abstract: Line capture devices for unmanned aircraft, and associated systems and methods are disclosed. A system in accordance with a particular embodiment includes a line capture device body having a line slot with an open end and a closed end. A retainer is positioned proximate to the line slot and has a rotor with a plurality of rotor arms positioned to extend at least partially across the line slot as the rotor rotates relative to the body. A joint rotatably couples the rotor to the body, and a ratchet device is operably coupled to the rotor to allow the rotor to rotate in a first direction and at least restrict the rotor arm from rotating in a second direction opposite the first. In other embodiments, the retainer can include other arrangements, for example, one or more wire-shaped elements.

Abstract: Liquid dispensing assemblies including adhesive anchoring assemblies configured to adhere to a support surface external to a device such as a vehicle. An air vehicle includes (a) a fluid adhesive container assembly detachably attached to the air vehicle, wherein the fluid adhesive container assembly comprises: (i) an adhesive container comprising fluid adhesive; and (ii) one or more fibers, wherein the one or more fibers are configured, or a brush of fibers, or a fabric of fibers, is configured to conduct the fluid adhesive and to structurally support an adhesive bond between the one or more fibers and a surface; and (b) means for dispensing the fluid adhesive from the fluid adhesive container, to the one or more fibers.

Abstract: An improved aircraft gate parking and servicing method is provided, wherein an aircraft is maneuvered into an airport terminal gate and parked in an optimum orientation at an angle that facilitates maximum access to aircraft front and rear doors. Boarding bridges are designed to facilitate connection to doors located rear of an aircraft wing without extending over the aircraft wing to maximize efficiency of passenger transfer. Passenger transfer and servicing of the aircraft may occur concurrently before the aircraft is maneuvered out of its optimum orientation in the parking space and driven to a takeoff runway for departure. Required safety margins are maintained at all times during aircraft maneuvers into and out of the optimum parking orientation. Stairs may be provided to simultaneously access aircraft doors not connected to boarding bridges. In a preferred embodiment, aircraft are moved to an optimum parking location by engines-off electric taxi systems.

Abstract: A method and apparatus for comparing aircraft parts. A first model is identified for a first aircraft for assembly. A second model is identified for a second aircraft that has been assembled. First parts for the aircraft in the first model are compared with second parts for the second aircraft in the second model. Graphical representations of the first parts and the second parts are displayed illustrating a difference between the first parts and the second parts from a comparison of the first parts and the second parts.

Abstract: A dispensing device for a flowable, in particular powdery product, includes at least one screw conveyor discharging the product, a drive for rotating the screw conveyor about its longitudinal axis, and a forming tube for guiding a tubular film. The screw conveyor protrudes with its longitudinal axis into the forming tube, wherein at least one screw guide, in which the screw conveyor is guided transversally to its longitudinal axis, is formed by the inner wall of at least one cylindrical recess in the forming tube.

Abstract: An apparatus for filling a syringe by transferring a viscous material from a container into the syringe includes a container having an interior that holds the viscous material and a plunger that expels the viscous material from the container. A syringe is connected to the container for receiving the viscous material at an entrance opening. The syringe includes a plug that separates the syringe into first and second sub-chambers and a rod contacting the plug and applying a force in the direction of the entrance opening. An assisting device assists in moving the rod away from the entrance opening as the first subchamber fills with the viscous material.