Abstract: An offshore drilling system includes a drilling tower, a tubular string hoisting device with a crown block and a travelling block suspended from the crown block in a multiple fall arrangement. A heave compensation system is adapted to provide heave compensation of the travelling block. The heave compensation system includes a hydraulic sheave compensator. The system further includes a mobile working deck which is movable with respect to the drilling tower within a motion range including a heave compensation motion range. The heave compensation system is further adapted to provide heave compensation of the mobile working deck by a hydraulic deck compensator, which is hydraulically connected via a hydraulic conduit to the hydraulic sheave compensator, such that in operation the deck compensator moves synchronously with the sheave compensator of the heave compensation system.

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 water mat assembly having selectively attachable modular panels is disclosed. The water mat comprises a buoyant solid core insert that is inserted into a sleeve made of fabric. The sleeve may be couple to other sleeves to form an assembly of floating panels. The end panels may have grommeted ports for tethering the mat assembly to a dock or water vehicle.

Abstract: A system for controlling a towrope winch may comprise a computing device configured to send and receive data to and from the towrope winch, and a towrope winch application configured to operate on the computing device, in which the computing device is configured to operate the towrope winch based on data inputted by the user to the towrope winch application. A towrope winch user interface may comprise a processor configured to send and receive data to and from a towrope winch, and a towrope winch application configured to operate with the processor, in which the processor is configured to operate the towrope winch based on data inputted by the user to the towrope winch application.

Abstract: What is provided is a propeller guard apparatus that may be readily configured to a variety of different boat motors. Described embodiments of the propeller guard apparatus comprise a cylindrical housing configured to circumferentially enclose a propeller from all sides in order to protect humans, pets, and aquatic wildlife from being entangled or cut by the propeller. Described embodiments of the propeller guard apparatus also comprise a protective structure, such as a skid plate comprising of at least two pieces of metal attached from the cylindrical housing to an end of the outer casing to form a folded T-shaped configuration. This type of configuration serves to protect the propeller from damage caused by submerged objects and aquatic wildlife found in shallow water. Also, the folded T-shaped configuration may push vegetation, weeds, manatees, and other aquatic wildlife away from the path of the moving boat and its propeller.

Abstract: The subject of the invention is a watercraft equipped with wheels of special design, which is capable of running on the surface of water. The vessel makes a novel maritime vehicle for fast transportation of small groups of people and commercial merchandise over the surface of rivers, seas, and oceans. The thrust, and share of the lift, is generated by hydrodynamic reaction of water to roll-and-slide motion of the wheels; the rest of the lift, which is necessary to counterbalance the loaded weight of the cruising vehicle, is generated by hydrodynamic forces acting on four plates with adjustable angle of attack and mounted on hydraulic struts with adjustable length. The wheeled watercraft, running on the surface of water at cruising speed, can surpass significantly planing vessels and hydrofoils in speed and fuel efficiency, and lower engine power required to achieve high speeds. The invention has the potential for a number of military applications.

Abstract: Upper anti-vibration mounts have axial lines arranged in parallel to a longitudinal center line extending in a longitudinal direction of the outboard motor body. Lower anti-vibration mounts have axial lines concentrated on one point on the longitudinal center line extending in a longitudinal direction of the outboard motor body. Meanwhile, the axial lines are inclined at the identical angle symmetrically with respect to the longitudinal center line, so that they intersect in a V-shape in front of the support shaft as seen in a plan view of the outboard motor body.

Abstract: A ballast water treatment apparatus equipped with devices for injecting bromine salt and ozone includes a ballast pipe, a ballast pump, a bromine salt injection part and an ozone processor, wherein the injection part includes a bromine salt storage tank; a bromine salt transfer pipe connected to the ballast pipe for injecting bromine salt supplied from the bromine salt storage tank into the ballast pipe; and a bromine salt injection pump in the transfer pipe for pressurizing bromine salt to be injected into the ballast pipe, and the ozone processor includes an ozone injection device for supplying ozone to the ballast pipe; a mixer in the ballast pipe for mixing ozone supplied from the ozone injection device and seawater transferred into the ballast pipe; and an ozone transfer pipe connected to the mixer of the ballast pipe for injecting ozone supplied from the ozone injection device into the ballast pipe.

Abstract: This invention, the Motor-wing Gimbal Aircraft (MGA) is an aerial vehicle and waterborne craft. It launches and lands vertically from the ground and water. In flight, it transitions from vertical, hovering and forward flight to horizontal flight. The MGA embodies multiple configurations and arrangements of motor-wings, propulsion systems and hybrid engine combinations. The MGA uses a fly-by-light system for flight maneuvering and controlling the motorized multi-axis gimbal cockpit. The MGA uses cellular communications together with the Global Positioning System (GPS) for navigation, collision avoidance and restricted airspace avoidance. The MGA uses visible lights to signal its elevation and flight maneuvers. The MGA is constructed of modular apparatuses and assemblies that are interchangeable and work in concert to power and maneuver the vehicle.

Abstract: A method of improving optical characteristics of an optical window operating in a flow of fluid and having first and second panes of optically transmissive material—each having an edge adjacent to, parallel with, and at least partially coextensive with each other—is described herein. The method includes inserting a thermally conductive blade between two adjacent edges of the first and second panes of optically transmissive material; and lifting an adverse flow stagnation zone forward of the optical window by protruding the thermally conductive blade into the flow of fluid from an outer surface of the panes of the optical window.

Abstract: A system includes a matrix material to remove heat from an object. The matrix material includes a plurality of vascular structures. Each of the vascular structures are filled with a fluid. At least one transducer generates field-induced forces into the fluid within the vascular structures of the matrix material. At least one controller pulses the transducer to generate the field-induced forces into the fluid within the vascular structures. The field-induced forces generate fluid flow within the vascular structures to remove the heat from the object.

Abstract: A winglet for attachment to a wing portion of an aircraft comprises a winglet tip and a winglet root opposite from the winglet tip. The winglet has an opening for receiving therethrough a connector for connecting the winglet to a wing portion in use. The winglet has a retainer internal of the winglet for use in retaining the connector relative to the winglet. The retainer has a hole that extends along an axis that passes through the opening for receiving therethrough a portion of the connector when the connector is located through the opening. The retainer comprising a body for reacting against a retention component with which the connector engages in use.

Abstract: A fuselage rear end of an aircraft, comprising a structural part comprising a skin and longitudinal and transversal reinforcing members and a fairing. The structural part longitudinally spans over the whole rear end and comprises a first portion in which the transversal reinforcing members occupy the whole perimeter of the corresponding fuselage section and at least a second portion in which the transversal reinforcing members occupy only a portion of the perimeter of the corresponding fuselage section. The fairing is located below the second portion of the structural part.

Abstract: In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of an aircraft. The first deflector may form part of a top surface of the aircraft when in a first closed position. The apparatus may further include a second deflector configured to couple to the shaft and form part of a bottom surface of the aircraft when in a second closed position. The first deflector and the second deflector may be configured to be positioned at a junction of a body of the aircraft and a wing of the aircraft. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

Abstract: In one embodiment, an apparatus includes a first deflector configured to couple to a shaft of a wing of an aircraft and form part of a top surface of the wing when in a first closed position, and a second deflector configured to couple to the shaft and form part of a bottom surface of the wing when in a second closed position. The first deflector and the second deflector may be configured to be positioned proximate to the tip of the wing. The first deflector and the second deflector may be configured to simultaneously pivot from the closed positions to respective first and second open positions upon actuation of the shaft.

Abstract: An assembly of two parts, one of the parts being made of composite material with fiber reinforcement obtained from a fiber preform made by three-dimensional weaving and densified with a matrix, the assembly including a mechanical anchor element secured to one of the parts and inserted inside the other part.

Abstract: A rotor head is provided and includes a non-rotating frame, a rotating frame rotatable relative to the non-rotating frame and configured to impart motion to the rotating frame, a rotor hub assembly rotatable about a rotation axis and including a hub and blades extending outwardly from the hub and being pivotable about respective pitch axes thereof and rocker assemblies respectively associated with corresponding ones of the blades. Each rocker assembly is interconnected between the rotating frame and the corresponding one of the blades and configured to convert the motion imparted to the rotating frame into a pitching of one of the blades about the respective pitch axes and amplify the motion such that an angle of the pitching exceeds an angle that would be achieved if the corresponding one of the blades were connected directly to the rotating frame.

Abstract: The force feedback device includes a stationary housing intended to be secured to an understructure of an aircraft, at least one spring opposing movement of a side-stick of the aircraft relative to the housing, and a transmission mechanism, which is supported by the housing movably and which is suitable for transmitting a rotational movement, around a first rotation axis, between the side-stick and said at least one spring, by applying a force law according to which a resistive force, opposed by said at least one spring, via the transmission mechanism, against the rotational movement of the side-stick around the first rotation axis, depends on an angular position of the side-stick around the first rotation axis.

Abstract: An apparatus is provided for dynamically controlling airflow behind a carrier aircraft to redirect air flow during an in-flight recovery of an unmanned aerial vehicle (UAV). The apparatus comprises a frame attached to an end portion of an arm member extending from the carrier aircraft. The apparatus comprises a plurality of vanes disposed within the frame. Each vane is controllable between an opened position and a closed position to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV. Alternatively, or in addition to, the apparatus comprises a plurality of compressed air jets disposed on the frame, wherein each jet is controllable to provide active airflow to dynamically modify the airflow behind the carrier aircraft during the in-flight recovery of the UAV.

Abstract: An apparatus, method and system for combining aerodynamic design with engine power to increase synergy between the two and increase climb performance, engine-out performance, and fuel efficiency for a variety of aircraft or the like.

Abstract: A winglet for attachment to a wing portion of an aircraft including a winglet root. The winglet root defines a recess for receiving a connector of the wing portion in use and includes at least one protrusion for receipt into at least one corresponding hole of the wing portion in use. A portion of the winglet root that at least partially defines an upper or a lower side of the recess has at least one hole extending therethrough for receiving a fastener for fastening the winglet to the connector when the connector is located in the recess.

Abstract: A telescoping strut for a retractable landing gear in an aircraft. The telescoping strut comprises a pre-pressurized and central extension chamber extending along the telescoping strut and a surrounding retraction chamber. For retraction, an hydraulic generation architecture of the aircraft feeds a single input/output passage of the surrounding retraction chamber with a overcoming fluid pressure that overwhelms a extension positive pressure in the central extension chamber and opposes the effect of the pre-pressurizing. The retraction system is for instance for a rotorcraft.

Abstract: A force generator includes a hub, which is rotatable about an axis thereof, an elongate member coupled to the hub such that the elongate member is rotatable with the hub and extends radially outwardly away from the hub and the axis along a radial dimension defined with respect to the axis and a mass, which is movably disposed along the elongate member and is adjustable to multiple radial mass positions relative to the hub.

Abstract: A stoppable rotor, which includes a first and second blade and rotates about a substantially vertical axis, is stopped with the first blade pointing forward and the second blade pointing backward while the aircraft is mid-flight. Anti-torque is provided using a set of one or more combination rotors in a first mode of operation in order to counter torque produced by the stoppable rotor when the stoppable rotor is rotating where the set of combination rotors rotate about a substantially longitudinal axis. Forward thrust is provided using the set of combination rotors in a second mode of operation when the stoppable rotor is not rotating.

Abstract: While an aircraft is mid-flight, a braking start point associated with a stoppable rotor is calculated where the stoppable rotor includes a first and second blade and the stoppable rotor is configured to rotate about a substantially vertical axis. A process to stop the stoppable rotor is started, while the aircraft is mid-flight, when the stoppable rotor reaches the braking start point, where the stoppable rotor is stopped with the first blade pointing forward and the second blade pointing backward.

Abstract: A multi-blade rotor for a rotary wing aircraft, comprising a plurality of rotor that is connected to an associated rotor head via a plurality of flexbeam elements, wherein at least one flexbeam element of the plurality of flexbeam elements comprises an asymmetrical flexbeam root that is mounted to the associated rotor head.

Abstract: A trim tab for use in a blade housing includes a cavity connected to an opening extending from the cavity out a trailing edge of the blade housing, the cavity has a first dimension which is greater than a second dimension of the opening at a same spanwise location of the blade housing. The trim tab has a trim portion, a head portion having a head dimension substantially similar to the first dimension, and a tail portion connecting the trim portion and the head portion. The tail portion has a tail dimension substantially similar to the second dimension such that the trim tab is retainable by the blade housing when the head portion is disposed within the cavity and the tail portion is disposed within the opening.

Abstract: A main rotor trim tab retention system includes, a blade housing having flanges separated by a cavity defined between the flanges, and a trim tab assembly. The trim tab assembly includes, a trim tab having an aerodynamic surface, at least one arm extending from the trim tab positionable within the cavity while the trim tab extends outward from the cavity, and a spherical bearing connecting the trim tab and the at least one arm, the spherical bearing having a first axis which is substantially perpendicular to the aerodynamic surface of the trim tab. The at least one arm is pivotable about the spherical bearing about a second axis substantially perpendicular to the first axis to rotate the trim tab relative to the blade housing.

Abstract: Provided are an unmanned aerial vehicle executing relief work in an emergency such as a disaster, a relief system, and a relief method for performing relief work by using an unmanned aerial vehicle. An unmanned aerial vehicle capable of performing autonomous flight includes a receiving unit receiving an input of relief work from a user A2 and a control unit controlling the execution of the relief work based on content of the input received by the receiving unit.

Abstract: An unmanned aerial vehicle for providing ameliorative action.

Abstract: Aspects of the disclosure include a method, system, and computer program for delivering a product. The method includes determining a delivery location and time for a payload using an aircraft. A recipient is notified of the delivery location and time. A first signal is received from the recipient. The time or location of the delivery location and time is changed, dynamically, based on the first signal. The payload is delivered to the recipient.

Abstract: An aircraft provided with a wing and a winch device. The winch device is provided with a hoist device that includes a storage drum and a motor member for winding a suspension member around the storage drum and for unwinding said suspension member off the storage drum. The hoist device is surrounded at least in part by a fairing of the winning, said hoist device being arranged in an inside volume of the wing at least in a position referred to as the “streamlined” position.

Abstract: An aerodynamically shaped, active towed body includes a fuselage curved along its vertical and horizontal longitudinal plane. The fuselage has a unit chamber and a load chamber. A transverse plane of the fuselage is triangular, two upper corners being located on an upper face of the fuselage and a lower corner being located on a lower face of the fuselage. Each of two wings is subdivided into a small and a large segment. The small segment points downwards and is attached to the fuselage in a region of the lower corner and the large segment points upwards and is attached to the small segment. Each of the small segments comprise an additional load chamber. The towed body further includes a tail fin, rudders that are each adjustable by the control device and a coupling for the towing cable.

Abstract: An aircraft monument comprising a desk and a movable part that is mounted to the aircraft monument by means of an attachment device. The movable part is pivotable about an axis between a first position in which the movable part covers a first area of the desk and is essentially arranged inside of the aircraft monument such that its front faces in a first direction towards the back of the aircraft monument, and a second position in which the movable part is at least partially arranged outside of the aircraft monument and its front faces in a second direction that crosses the first direction. The movable part, in its second position, covers a second area of the desk that is less than the first area.

Abstract: An arrangement for selectively arresting a serving trolley in a cabin includes a walling extending perpendicularly to a cabin floor. The walling has a height at least equal to the height of a serving trolley. The arrangement has an upper arresting unit positioned at an upper fastening section of the walling and a lower arresting unit positioned at a lower fastening section of the walling. The upper arresting unit has a first engagement element and a second engagement element, wherein at least one of the engagement elements is movable relative to the other engagement element. The upper arresting unit releasably engages two distanced recesses at an upper end of the serving trolley by way of the engagement elements. The lower arresting unit includes at least one third engagement element and is designed for engaging a bottom side component of the serving trolley by way of the third engagement element.

Abstract: Described are adjustable seats having a lower portion of a back rest attached to a seat frame having an upper frame and a lower frame. A pivot axis is positioned at an upper end of the lower portion of the back rest, and an upper portion of the back rest is pivotally attached to the pivot axis. The location of the pivot axis is configured to be positioned below a person's shoulders when the person is seated in the adjustable seat. The upper portion of the back rest is also pivotally adjustable relative to the lower portion of the back rest. A seat pan having a front portion pivotally coupled to a rear portion can be attached to the upper frame. An actuation mechanism is configured to simultaneously control a vertical height of the upper frame and a rotational position of the front portion of the seat pan.

Abstract: A flight attendant seat comprises a carrier having a guide with opposed first and second ends, and a storage compartment receiving the guide first end. The guide provides guidance along its length between its first and second ends. The seat comprises a plurality of segments, each slidingly mounted to the guide to allow a sliding movement of the segments along the guide and relative to the carrier device between a stored position of the segments within the storage compartment, and an exposed position of the segments. A seat element is pivotally mounted to a first of the segments pivotable between an inoperative and operative seat forming position. At least one backrest is mounted to at least a second of the segments. With the segments in their exposed position, the seat element, when pivoted to its operative position, together with the backrest(s), can be used as a flight attendant seat.

Abstract: A seat system for a cabin of a transportation system includes a first seat unit, a second seat unit, and a rail system attachable to a floor of the cabin, having two rails that run parallel to each other, for receiving the seat units on selective positions. A line-up of a plurality of first seat units and at least one second seat unit on the rail system constitutes a seat arrangement. The first seat unit includes a seat frame having a seat cushion and a back cushion. The second seat unit includes a seat frame having a foldable seat cushion and a back cushion. The second seat frame includes two forward seat legs supported on two auxiliary rail segments that are arranged between the rails in a region. The forward seat legs are guidable underneath the seat cushion of a first seat unit arranged in front of it.

Abstract: A vehicle cabin seat arrangement includes a seat rail having a first and a second side faces; a group of passenger seats held on the seat rail by holding devices resting on a top side of the seat rail; pluralities of first and second holding blocks arranged on the first and second side faces, respectively; and a plurality of stop blocks arranged on a bottom side of a holding device To every passenger seat two first or second holding blocks are assigned, between which a holding device coupled with the passenger seat is displaceable. The respective holding device, includes one of the stop blocks arranged on the bottom side of the holding device such that the stop block is bringable into contact with the two assigned holding blocks on moving the holding device on the seat rail. Passenger seats are alternatingly assigned with first and second holding blocks.

Abstract: A vehicle cabin seat rail system includes a seat rail having a top side having a plurality of raster openings and mechanically couplable with a cabin floor, a plurality of holding devices positionable on the top side, each being selectively engageable with at least one first raster opening or at least one second raster opening for arresting the holding device and configured for holding an object on the seat rail, and a plurality of marking devices couplable with the seat rail, and configured for optically or mechanically indicating approaching of a first position on the seat rail corresponding to the first raster opening of a respective holding device and of a second position of the same holding device corresponding to the second raster opening, in relation to another object arrested on the seat rail, to prevent an arresting of the holding device on the seat rail on other positions.

Abstract: A compressor temperature control system and method for an aircraft air cycle machine is presented. The system prevents overheating of the compressor using a low limit valve positioned between a turbine outlet and a bleed air source. The low limit valve directs the air to an air cycle machine, or bypasses the machine, in regards at least in part to the air temperature measured in the cabin supply duct.

Abstract: An airplane is provided. The airplane includes a first medium at a first pressure, a second medium at a second pressure, a third medium at a third pressure; and an air conditioning system. The air conditioning system includes a compressor, a first heat exchanger configured to transfer heat from the first medium to the third medium, a second heat exchanger configured to reject heat from the first medium, a third heat exchanger configured to reject heat from the second medium, a first turbine configured to receive the first medium, and a second turbine configured to receive the second medium.

Abstract: An airplane is provided. The airplane includes a compressing device including a turbine and a compressor. The turbine includes first and second inlets and provides energy by expanding one or more mediums. The first inlet is receives a first medium of the one or more mediums. The second inlet receives a second medium of the one or more mediums. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode.

Abstract: An airplane is provided. The airplane includes a compressing device. The compressing device includes a turbine with a first inlet and a second inlet. The turbine provides energy by expanding mediums. The first inlet is configured to receive a first medium of the mediums. The second inlet is configured to receive a second medium of the mediums. The compressing device includes a compressor and a motor. The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode.

Abstract: An airplane is provided. The airplane includes a pressurized volume and an air conditioning system. The air conditioning system includes a compressor configured to receive a flow of a first medium, a turbine downstream of the compressor in a flow path of the first medium, a first valve that diverts the flow of the first medium around the turbine, a second valve that provides a second medium to the turbine, and a third valve downstream of the turbine that directs an outlet flow of the turbine towards the pressurized volume and that directs the outlet flow of the turbine away from the pressurized volume.

Abstract: A filter assembly including a plurality of filter modules, wherein each filter module in the plurality of filter modules includes a frame, a filtration element coupled within the frame, and at least one mating feature. The at least one mating feature of each filter module is configured for selective engagement with the at least one mating feature of another filter module such that the plurality of filter modules are coupled together in a serial arrangement.

Abstract: Disclosed is an air mix valve including: a wall having at least three openings; and at least one airflow-regulating device. The airflow-regulating device includes: at least two shutters placed in the internal volume of the valve, at least one aerodynamic shutter of which is arranged with respect to one of the openings so as to be able to receive an airflow passing through this opening, and a linking mechanism between at least two shutters. Each of the shutters is arranged and guided so as to be able to be caused to move with respect to the wall. At least one airflow-regulating device, named aero-controlled regulation device, is mounted to be freely movable under the effect of aerodynamic energy from airflows passing through the openings.

Abstract: An air cycle machine is provided. The air cycle machine can be included an environmental control system of an aircraft. The air cycle machine can include a turbine comprising a plurality of inlet gas flow paths, a compressor driven by the turbine from a shaft, and a fan driven by the turbine from the shaft.

Abstract: An air cycle machine for an environmental control system for an aircraft is provided. The air cycle machine includes a compressor configured to compress a first medium, a turbine configured to receive second medium, a mixing point downstream of the compressor and downstream of the turbine; and a shaft mechanically coupling the compressor and the turbine.

Abstract: An air conditioning system for an aircraft is provided. The air conditioning system includes a first rotating component and a second rotating component. The first rotating component includes a compressor and a turbine. The compressor pressurizes a first medium. The first turbine receives a mixture of a second medium and a pressurized form of the first medium. The second rotating component includes a fan.