Abstract: Oil tanker and or ore/oil carrier can take more good fuel oil consumption through cargo oil handling by usage of electric motor driven system instead of steam turbine driven cargo pump system. Its merit is about 20%.

Abstract: The invention relates to a rescue device for a container (7) having container corners (9) loaded onto a damaged ship (110), comprising a crane (50) arranged on a carrier (20, 21, 22), wherein the crane (50) has a front support arm (51), over which a load cable is guided, whose section leading away from the support arm (51) is connected to a container (7) to be unloaded, and the length of which can be changed. The invention is characterized in that the carrier (20, 21, 22) has at least one locking mechanism (204, 205) located opposite the crane (50), by means of which the carrier (20, 21, 22) is temporarily fastened in a releasable manner at the container corners (9) of at least one of the containers (7) fastened on the deck (1) of the damaged ship (110).

Abstract: The present invention includes a surfboard comprising a laminated frame extending along the side rails of the surfboard, the laminated frame comprising three or more layers of laminates, and wherein the laminated frame has been formed to the shape of the rocker of the surfboard. In various exemplary embodiments, the laminated frame may have one or more lateral members extending between opposing sides of the laminated frame, wherein such lateral members may be circular in cross-section, and may include one or more supports connecting the lateral members to the top surface of the surfboard. In various exemplary embodiments, two or more layers of laminates may form an internal structure extending laterally across the laminated frame from one side to the other.

Abstract: A harness for wind sports has a rigid, external composite frame that contours to a region of a user's back. Direct connections between the composite frame and a spreader bar facilitate transmission of forces. The spreader bar may have a rope to provide a sliding attachment point to a sail or kite.

Abstract: A multiple services system through sensors having a central monitoring unit for vessels, consisting of a central monitoring unit and a set of sensors being connected to each other in a wireless way, and being susceptible to establish communication through the central monitoring unit with a remote user.

Abstract: A buoyant apparatus and method of use buoyancy to offset the weight of a load during immersion of the load in a fluid medium such as a payload manipulated by a cable and crane or by a remotely operated undersea vehicle. Buoyancy modules that can be of different size and shape have elongated supports that are attachable via complementary connection fixtures at the ends. The attached supports form a skeleton of the array. The connection fixtures are axially resiliently compressible and maintain the buoyancy modules in abutment notwithstanding shrinkage or expansion of the buoyant material due to hydrostatic pressure that increases with depth.

Abstract: The disclosure relates to a fluid outlet interface for a personal watercraft, so that the latter can collect and divert a very small portion of the fluid pressurized by said vehicle and thus create a sufficient Venturi effect to drive the emptying of the bilge of said vehicle. The disclosure also relates to a personal watercraft, or more generally any floating device delivering a pressurized fluid, comprising such an interface.

Abstract: The present disclosure discusses a method of and an arrangement for the lubrication of a controllable pitch propeller of a marine vessel. The lubrication is based on continuous lubricant circulation from the hydraulic powerpack to the hub and back to the oil tank, when the marine vessel is sailing ahead with propeller blades locked in a desired position. The lubrication is performed by maintaining, at least when the propeller blades are locked in a desired position, a pressure difference between the astern oil chamber and the lubricant chamber for circulating lubricant from the astern oil chamber via the lubricant chamber to the oil tank.

Abstract: The present technology is directed generally to electric marine propulsion systems with drive trains, and associated systems and methods. In representative embodiments, the disclosed technology includes pre-assembled transmission cartridges, gear reduction planetary gears, and/or component support arrangements that can increase the life of the system and/or reduce manufacturing costs.

Abstract: Provided is a ship propulsion system such that an increase in the size of a main engine can be minimized. The ship propulsion system is equipped with: main generators that supplies power to the interior of a ship; a power distribution unit that distributes the power of the main generators; a first electric motor that rotatably drives a first rotary shaft with the power input through the power distribution unit; a main propeller that rotates along with the first rotary shaft; a second electric motor that rotatably drives a second rotary shaft with the power input through the power distribution unit and a stern-side propeller that is disposed on the stern side of the main propeller and rotates along with the second rotary shaft.

Abstract: An exhaust system for a watercraft with an engine includes an upstream exhaust pipe including an end portion with an outlet, a water lock including an inner space accommodating the end portion, a downstream exhaust pipe connected to the water lock, and a flow direction diverter, such as a baffle. The upstream exhaust pipe guides exhaust gas from the engine to the end portion. The inner space of the water lock receives the exhaust gas from the outlet of the end portion. The downstream exhaust pipe exhausts the exhaust gas from the inner space to an outside of the watercraft body. The flow direction diverter changes a flow direction of the exhaust gas at the outlet to a cross direction which intersects a pipe axis of the end portion.

Abstract: Disclosed is a water intake system for a floating vessel in a body of water, which includes within the hull of the vessel an intake compartment for taking in water from the body of water and a distribution compartment for distributing and supplying the water to one or more consumer units within the floating vessel. The intake compartment is arranged below a lowest operational draught of the vessel and has an inlet in a bottom region of the intake compartment. The intake compartment is coupled by a conduit to the distribution compartment for allowing water to flow into the distribution compartment. The water intake system further includes a water lift hose that is connected to the inlet and is extendible below the hull of the vessel.

Abstract: A method for operating a cooling system of a ship, having a sea water part system with a sea water pump (14a, 14b) and at least one first cooling water circuit. The first cooling water circuit includes a bypass in a heat exchanger coupling the sea water part system and the first cooling water circuit and a control valve. A position of the control valve determines a cooling water proportion of the first cooling water circuit that is conducted via the heat exchanger and a cooling water proportion of the first cooling water circuit that is conducted via the bypass. The position of the control valve is controlled such that an advance cooling water temperature corresponds to a set point value. The rotational speed of the sea water pump is controlled based on the position of the control valve.

Abstract: A composite material that includes a layer of reinforcing fibres impregnated with a curable resin matrix and a plurality of electrically conductive composite particles positioned adjacent or in proximity to the reinforcing fibres. Each of the electrically conductive composite particles is composed of a conductive component and a polymeric component, wherein the polymeric component includes one or more polymers that are initially in a solid phase and are substantially insoluble in the curable resin, but is able to undergo at least partial phase transition to a fluid phase during a curing cycle of the composite material.

Abstract: Systems and methods for assembling a structurally reinforced composite structure are disclosed herein. The methods include deforming a composite tubular skin to a deformed conformation to generate clearance to permit a frame assembly to be conveyed into an internal volume that is defined by the composite tubular skin. The methods further include conveying the frame assembly into the internal volume, permitting the composite tubular skin to deform from the deformed conformation to the target conformation, and operatively attaching the frame assembly to the composite tubular skin to form the structurally reinforced composite structure. The systems include a frame support that is configured to support the frame assembly, a frame deformation assembly, a skin support that is configured to support the composite tubular skin, and a skin deformation assembly.

Abstract: Presently disclosed sliding joint kits, sliding joints, and systems including the same may be configured to join a first panel and a second panel together such that at least a portion of the first panel and second panel are in sliding contact with one another, thereby allowing movement of one panel with respect to the other. In this manner, panels may be joined together while still allowing thermal expansion and resulting movement of one panel relative to the other. For example, presently disclosed sliding joints may be used to join panels of an aircraft heat shield together, which may result in reduced buckling and/or reduced joint stress of the panels of the heat shield. Related methods of assembling a sliding joint kit to join a first panel and a second panel are also disclosed.

Abstract: Reinforced wing spars for underwing mounted retractable landing gear assemblies include a unitary (one-piece) metal wing spar having a central web and an upper spar flange, a trunnion mounted in the web of the wing spar for pivotally receiving a transverse mounting tube of a retractable landing gear strut, and a reinforcement laminate adhered to and extending along the upper spar flange above the trunnion, wherein the reinforcement laminate is comprised of at least one fiber reinforced composite layer alternately interposed with at least one metal reinforcement layer.

Abstract: An actuator hardover monitor for a control surface includes an actuator sensor for detecting an actuator position, a command model of an expected position of the actuator based on an input command, and a monitor to determine whether a difference between the actuator position and the expected position exceeds a threshold for a predetermined duration. A method of preventing a hardover event for a control surface includes commanding an actuator valve to a commanded position, determining continuously when the commanded position, or an actuator valve position, or a control-surface position, or a modeled actuator valve position exceeds a predetermined limit to provide an exceedance. The method may further include filtering a signal of the exceedance based on a time constant to provide a filtered exceedance, and switching to a backup control-surface actuator when the filtered exceedance exceeds the predetermined limit for a predetermined duration.

Abstract: Apparatus for obstructing air flow through an aperture in an aircraft wing where a movable anti-icing duct extends through the aperture are disclosed. An exemplary apparatus comprises a base member (40) configured to be secured to the duct and a first seal member (42) configured to obstruct air flow through the aperture. The first seal member comprises a proximal portion (42A) connected to the base member and a distal portion (42B) configured to movably contact an inner surface of a skin of the wing. The use of such apparatus may reduce the amount of leakage flow from the high pressure lower wing surface to the low pressure up per wing surface through the aperture and thereby reduce the loss of lift associated with such leakage flow.

Abstract: A spinner assembly includes a cone-shaped member having a plurality of blade openings. The cone-shaped member is receivable about a shaft at a first location. A bulkhead frame is connected to the cone-shaped member. At least one strut is configured to couple the bulkhead frame to the shaft at a second location. The at least one strut includes at least one arm having a longitudinal rigid member and at least one flexure region that defines an axis about which the at least one arm bends.

Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.

Abstract: A propeller includes a blade free to rotate about a longitudinal axis of the blade. The propeller also includes a mechanical stop positioned to engage mechanically a first portion of the blade and/or a first structure coupled mechanically to the blade when the blade is in a first position. The propeller also includes a magnetic stop positioned to engage magnetically a second portion of the blade and/or a second structure coupled mechanically to the blade when the blade is in a second position. The blade rotates to the first position against the mechanical stop when the propeller is rotated at a first rotational speed and the blade rotates to the second position against the magnetic stop when the propeller is rotated at a second rotational speed in a same direction as when the blade is in the first position.

Abstract: Proposed method and device could be applied as controlling system facilitating the maneuverability and stabilization parameters of UAV, as well as various flight objects and small satellites. The aim of the invention is to reduce the occurrences of imbalances of UAV in strong wind or atmospheric turbulence situations and simultaneously rehabilitation of maneuverability and stabilization parameters without increasing flight speed. Thus, in order to upgrade the above mentioned parameters of UAV along with the gyroscopic momentum compensation it's necessary to increasing of the kinetic moment by means of gyroscope.

Abstract: An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency.

Abstract: A downlock actuator may comprise an electric motor, a gearbox coupled to the electric motor, the gearbox comprising a rotary output shaft, and a connecting output shaft having a first end and a second end, the first end being coupled to the rotary output shaft of the gearbox, wherein the connecting output shaft is configured to rotate between a shaft locked position and a shaft unlocked position, wherein the gearbox is back-drivable in response to the connecting output shaft being in the shaft unlocked position.

Abstract: A locking linkage system may comprise a lockable assembly comprising an upper brace, a lower brace coupled to the upper brace, and a linkage coupled to the upper brace and the lower brace. The locking linkage system may further comprise a downlock actuator comprising an electric motor coupled to the upper brace, a rotary output shaft coupled to the electric motor, a connecting output coupled to the rotary output shaft, wherein the connecting output shaft is configured to rotate between a fixed locked position and a fixed unlocked position, and a link rod having a distal end coupled to the linkage and a proximal end comprising a lost-motion joint, the lost-motion joint being coupled to a connection pin of connecting output shaft. The downlock actuator may be configured to toggle the linkage, the upper brace, and the lower brace between an unlocked position and a locked position.

Abstract: In some embodiments, a rotorcraft includes an engine, a rotor hub assembly mechanically coupled to the engine and a plurality of rotor blade assemblies rotatably mounted to the rotor hub assembly. Each of the rotor blade assemblies includes a rotor blade having a leading edge and an erosion shield system extending spanwise along the leading edge of the rotor blade. The erosion shield system includes a plurality of erosion shield segments positioned adjacent to one another forming joints therebetween wherein, the joints deform responsive to strain experienced by the rotor blade, thereby isolating the erosion shield segments from at least a portion of the strain experienced by the rotor blade.

Abstract: A rotor blade system includes a hub assembly pivotally attached to a rotor blade, a mast attached to the hub assembly, and a swashplate engaged with the mast, the swashplate includes a non-rotating ring and a rotating ring. The method to raise the swashplate includes using an anti-drive link system pivotally engaged with a transmission top case and pivotally engaged with the non-rotating ring.

Abstract: According to one embodiment, a linear control motor includes a first permanent magnet, a coil, a shaft, a first non-magnetic material, and a joint coupled between the shaft and a spool operable to convert rotations of the shaft into axial movements of the spool. The first non-magnetic material is disposed between at least one of the movable components and at least one of the static components and operable to prevent physical contact between at least one of the movable components and at least one of the static components.

Abstract: A method of optimizing sections of a tail boom for a rotary wing aircraft, and also to a tail boom including such sections. The method comprises the step of creating a database characterizing standard sections for a tail boom that give precedence to minimizing a negative lift and/or to increasing a lateral force generated by the air stream from the main rotor of the aircraft flowing over the tail boom, a step of establishing looked-for aerodynamic and structural characteristics for said tail boom, and a step of defining the sections of the tail boom as a function of the standard sections and of the looked-for aerodynamic and structural characteristics. The tail boom as defined in this way optimizes the reduction in the negative lift and/or the increase in the lateral force generated by the air stream from the main rotor.

Abstract: Disclosed is an aerodyne including a supporting structure, to which are connected: at least one supporting axial blower, attached to the supporting structure; at least one main engine driving the supporting blower; at least three attitude blowers controlling roll and pitch, each attitude blower having an electrical motor and being attached, respectively, to one of the elongate arms that are distributed in a laterally, outwardly projecting manner around the supporting structure, to which each arm is connected by an inner end portion, the axis of rotation of each attitude blower being attached relative to the supporting structure, and all the attitude blowers being located outside the space centrally occupied by the supporting blower; at least one battery for supplying power to the electrical motors of the attitude blowers; a landing gear attached under the supporting structure; and a nacelle for holding the battery and a payload.

Abstract: Not requiring aileron, elevator, rudder, flap, slat, horizontal and vertical stabilizer and not transferring vibration to the fuselage In this invention the engine and fuselage (hanging under wing) are the same as those in other airplane but the wing (just one) is different, It has rectangular shape with triangular leading edge and consists of wing box(embedded in wing) to which four rotating taper tubes are attached, each with a propeller, that is, one pair for each side of wing box. There are two turbo shaft engines, each engine runs one pair of propellers, via shafts and gear boxes. Now smooth rotation of taper tube will tilt the propeller up to 90? using stepper motor, so propeller can tilt from horizontal (takeoff and landing) mode to vertical(cruise)mode.

Abstract: This is the Mano Supersonic Cockpit wish is the cockpit of a supersonic passenger aircraft place in as far front of the nose of the aircraft as possible to avoid the need for the nose of the supersonic aircraft dropping for landing and then straightening out for supersonic flight.

Abstract: Various methods for utilizing an unmanned aerial vehicle (UAV) to monitor hazards for a user may include maintaining the UAV at a monitoring position relative to the user, monitoring an area surrounding the user for approaching objects, detecting an approaching object, determining whether the approaching object poses a danger to the user, and performing one or more actions to mitigate the danger of the approaching object in response to determining that the approaching object poses a danger to the user.

Abstract: Cargo handling systems and methods for a freight deck of an aircraft are provided, as well as mobile transport apparatus. In at least one example, the system includes a support structure, at least one mobile transport apparatus, and a plurality of locking devices. The support structure is configured for at least partially supporting at least one cargo unit on the support structure, Each mobile transport apparatus is configured for selectively moving over the freight deck to a plurality of locations on the freight deck, for selectively engaging to the at least one cargo unit, for selectively propelling said at least one cargo unit over said freight deck while the apparatus is engaged to the at least one cargo unit, for enabling said at least one cargo unit to be deposited at a desired said location supported on said support structure, and for selectively disengaging from the at least one cargo unit.

Abstract: Embodiments of the present invention provide a water management system for use on board a passenger transport vehicle. The water management system may be used to address and manage excess humidity, water leaks, or any other instance when water or other liquid may collect at a certain location. The disclosure provides a system for managing excess water and for optionally delivering the water to another location. The removal location may be a disposal outlet or it may be a beneficial use of the collected water on-board the vehicle.

Abstract: A bucket for use with an aircraft storage bin that includes a bottom and first and second opposing side walls extending upwardly from the bottom. The first and second side walls each include a top edge. The first side wall includes a first slot that is open to the top edge of the first side wall and is configured to receive a first pivot axle therein, and the second side wall includes a second slot that is open to the top edge of the second side wall and is configured to receive a second pivot axle therein.

Abstract: A system for disposing waste in a transportation system includes a collection device for collecting waste in the cabin of the transportation system, a separate receptacle device for receiving collected waste from the collection device, and a connection device for selectively connecting the collection device to the receptacle device in order to deliver collected waste from the collection device into the receptacle device. The receptacle device is arranged in a lower deck region underneath the cabin floor. The connection device extends into the receptacle device from the cabin floor and includes a closure that is arranged on or in the cabin floor. The collection device is mechanically couplable to the connection device, and includes a closable output opening aligned with the closure of the connection device in the coupled state. The closure and/or the output opening can only be opened when the collection device is coupled to the receptacle device.

Abstract: A passenger cabin area, which is suitable for installation in an aircraft cabin, includes passenger seats arranged one behind another along a longitudinal axis of the passenger cabin area. The passenger cabin area also includes luggage compartments which are arranged, at least in certain sections, in an area between an inner face, which faces towards an interior space of the passenger cabin area, of a fuselage sidewall and the passenger seats, and have an access aperture which faces towards the passenger seats.

Abstract: A seat arrangement for a vehicle has: parallel aisles in a longitudinal direction of a cabin; cabin walls arranged parallel to the aisles; a central region enclosed by the aisles; and two outer regions neighboring the central region and separated from the central region through the aisles. Seat rows having two inner seat modules and two outer seat modules, are arranged in the central region behind each other. Additional seat rows having an inner seat module facing the respective aisle and an outer seat module wall facing the respective cabin wall, are arranged behind each other in the outer regions. Each seat module has a seat and an ottoman. The seat modules of the central region have a use direction aligned parallel to a main extension direction of the bordering aisle or enclose a maximum angle such that the ottoman reaches further into the aisle than the assigned seat.

Abstract: A seat arrangement includes a first group of seats having first and second passenger seats, a second group of seats having third and fourth passenger seats, a first aisle parallel to a longitudinal axis, and a second aisle parallel to the longitudinal axis. The first passenger seat is situated next to the first aisle with a seat direction parallel thereto, and the fourth passenger seat is situated next to the second aisle with a seat direction parallel thereto. The seat direction of the second passenger seat is angled by at least 2° relative to the seat direction of the first passenger seat. The seat direction of the third passenger seat is angled by at least 2° relative to the seat direction of the fourth passenger seat. The first and second groups are next to each other, and have a longitudinal offset relative to each other along the longitudinal axis.

Abstract: Aircraft, vibration isolation assemblies, and methods of assembling vibration isolation assemblies are provided. An aircraft includes a vibration isolation assembly. The vibration isolation assembly includes a mounting track, a plate, a clamp block, a vibration isolator, and a support fitting. The mounting track defines a cavity and includes flanges that define an opening to the cavity. The plate is configured to be positioned on the flanges outside of the cavity. The clamp block is configured to be fastened to the plate under the flanges of the mounting track within the cavity. The vibration isolator is configured to be laterally constrained by the clamp block within the cavity. The support fitting is configured to be secured to the vibration isolator outside of the cavity.

Abstract: A system and method for aircraft passenger seating allows traditional passenger seats, which have fixed configurations, to meet new specifications. A bottom frame and backrest frame from a traditional passenger seat is used to form a new passenger seat. Features, such as improved cushioning, telescopic or fixed headrests, rotatable or fixed footrests and improve armrest assemblies may be added as part of the new passenger seat.

Abstract: A seat module includes a passenger seat attachable to a cabin floor, and a separate ottoman unit associated with the passenger seat. The ottoman unit has at least one resting surface for a passenger and a base, which base is attachable to the cabin floor by an adjustment unit at a position in a first direction of the passenger seat. The adjustment unit is configured to allow a selective displacement of the ottoman unit relative to the cabin floor along the first direction and at least a second direction perpendicular thereto into a seating position and a resting position of the seat module.

Abstract: Apparatus and methods for providing a desired volumetric conditioned airflow rate and for reducing noise level, airflow recirculation and airflow separation are disclosed. An example apparatus includes a nozzle housing having a pair of opposing sidewalls and a front and back wall that define an airflow passage. The airflow passage has a centerline extending between the inlet and the outlet and has a plurality of cross-sections taken perpendicular to the centerline that collectively define a smooth contour along a length of the airflow passage. The cross-sections each have a thickness between the front and back wall that is greater at side edges than at the centerline. The thickness of the cross-sections decreases along a length of at least a first portion of the nozzle housing. A width of each of the cross-sections between the sidewalls increases along the length of at least the first portion of the nozzle housing.

Abstract: Systems and methods for aerially delivering cargo into a body of water while avoiding parachute entrapment and entanglement are described. The system includes a parachute having a canopy and suspension lines. The system further includes a weight coupled to a first end of the suspension lines and a ring that is configured to float in the body of water. The weight is coupled to the cargo, and the ring is disposed between the weight and the canopy with the suspension lines passing through the center of the ring.

Abstract: A liner assembly includes a core and a septum coupled to the core. The liner assembly also includes a facesheet coupled to the septum. The facesheet includes a plurality of slots defined therethrough. Each slot of the plurality of slots includes a major axis oriented perpendicular to a centerline of the liner assembly.

Abstract: A system and method for mounting a section onto a substrate, the system comprising: a fluid channel including: a fluid channel inlet that receives the section, processed from a bulk embedded sample by a sample sectioning module positioned proximal the fluid channel inlet, a section-mounting region downstream of the fluid channel inlet, and a fluid channel outlet downstream of the section-mounting region; a reservoir in fluid communication with the fluid channel outlet; and a manifold, fluidly coupled to the reservoir, that delivers fluid from the reservoir to the fluid channel inlet, thereby recirculating fluid flow between the fluid channel inlet and the fluid channel outlet to carry sections between the sample sectioning module and the section mounting region.

Abstract: An electrical architecture for an aircraft having a primary three-phase electrical network powering a transformer-rectifier unit serving to power two secondary DC electrical networks. Each of the two secondary electrical networks includes a contactor electrically connected to a generator-starter. The contactors are linked in pairs to prevent them from being closed simultaneously. The second secondary network powers the generator-starter to start a fuel-burning engine. The first secondary network can be powered by the generator-starter to power electrical components. A secondary voltage of the second secondary electrical network is greater than the voltage of the first secondary electrical network, thus making it possible to optimize the weight of the electrical architecture. The two secondary electrical networks may also be powered from autonomous sources of electricity as a replacement for the primary network to power the generator-starter and the electrical components.

Abstract: A heating system for a ram air turbine includes a heated screen that is disposed across an air inlet defined by a strut. The strut has a first end that is connected to a generator that is operably connected to a turbine that is connected to a second end of the strut. The heated screen has a heating element embedded therein.