Abstract: A coupling bushing includes a bushing body and a retainer for locking a coupling plug into the bushing body. The bushing body has a connecting section and a coupling section, wherein the connecting section and the coupling section are fluidically connected with each other via an inner channel. A bushing valve is arranged in the inner channel (8), wherein the bushing valve (10a) comprises a valve holder, an axially movable valve body and a valve seat. The retainer has at least one latching element, wherein the at least one latching element has a resiliently elastic design. The at least one latching element is designed to engage with a coupling plug.

Abstract: The present disclosure is directed generally to firewall seals for sealing pass-through members extending through a firewall, such as a firewall of a turbine engine. In one example aspect, the firewall seal includes quick-connect features that facilitate more efficient assembly and disassembly of the firewall seal to and from the pass-through member. Particularly, the firewall seal may define a slit extending through at least a portion of the seal that allows for the pass-through member to be slid through the slit and positioned in place. A retainer formed of an elastomeric material may include a metal spring plate that springs the seal back into place after the pass-through member is positioned within the seal. Moreover, a spherical bearing of the firewall seal may include features for receiving a static or dynamic pass-through member therethrough and for allowing the pass-through member to translate and rotate.

Abstract: A drill cuttings processing system including a breaker mill. The breaker mill operates to pulverize drill cuttings. The breaker mill includes an outer housing, a drum operatively positioned in the outer housing, hammers operatively positioned in the drum, and a screen configured for discharge of pulverized drill cuttings. A method includes feeding drill cuttings to the breaker mill. The breaker mill is located at a drilling rig site or is attached to a drilling rig. The method includes pulverizing the drill cuttings within the breaker mill.

Abstract: A standpipe assembly for a rotorcraft includes a slip ring positioned within the mast of the rotorcraft. The slip ring includes a stator rotationally connected to a rotor. A flexible coupling is connected to the stator and a standpipe tube is connected to the flexible coupling. The flexible coupling is capable of angular, axial, and torsional displacement.

Abstract: The invention refers to a quick released system for coupling (1) and drogue (2) assembly comprises a crown coupling connector (4) suitable for being fixed to the coupling (1) and comprising cavities (14); a plurality of balls (3) housed in the cavities (14) with an emerging part and radially movable; a crown drogue connector (5) suitable for being fixed to the drogue (2), configured to engage and disengage the coupling connector (4) and comprising first recesses (26); and a crown locking ring (6) rotatable between a locked and a released position and comprising second recesses (31). The second recesses (31) are arranged in correspondence with the first recesses (26) when the system is in a released position and, the locking ring (6) in contact with the balls (3) and the first recesses (26) engaged with the emerging part of the balls (3) when the system is in a locked position.

Abstract: An aircraft auxiliary fuel tank system comprising a master tank and a plurality of slave tanks connectable to the master tank. The slave tanks can be easily added or removed to adjust fuel capacity. A rail assembly is provided to assist in the easy installation and removal of the slave and master fuel tanks. Methods are provided for using the auxiliary fuel tanks system and for providing a service for slave tank distribution, reservation and installation.

Abstract: A drain mast includes a first fairing body defining a first fairing wall and a first drain portion. A second fairing body defines a second fairing wall and a second drain portion. The first and second fairing bodies are joined together as a fairing with the first and second fairing walls as opposed exterior fairing walls, and with the first and second drain portions joined to form a drain passage through the fairing from a drain passage inlet to a drain passage outlet.

Abstract: The invention relates to a device for receiving liquids in an aircraft and/or releasing liquids therefrom, especially during the flight, said device being arranged especially in an airplane. The aim of the invention is to provide a device which can receive large quantities of liquids in a rapid, reliable and flexible manner. To this end, the device can include a tank module with at least one tank container that is connected to a collector using a connecting shaft and a bulkhead module that can be connected to the tank module by the collecting tank. A closing element in the open position releases liquid from the tank module. In addition, a refueling module which is connected to the tank module by a supply line and a tube arranged on a winding device, and a receiving element attached to the tube, can provide refueling of the device.

Abstract: A fuel tank installation comprising: a fuel tank for holding fuel, the fuel tank comprising a fuel tank wall formed with a hole; a fuel pump assembly fitted into the hole in the fuel tank wall with an inner part of the fuel pump assembly protruding from an inner side of the hole and an outer part of the fuel pump assembly protruding from an outer side of the hole; a cage surrounding the outer part of the fuel pump assembly; and a mounting piece which attaches both the cage and the fuel pump assembly to the fuel tank wall.

Abstract: A water system for a vehicle is provided. The water system comprises at least one water supply source, at least one water-conducting device, at least one closing valve and at least one germ reduction connection. The germ reduction connection and the water supply source are connected to the water-conducting device. The germ reduction connection is designed to introduce a germ-reducing fluid into the water-conducting device. The closing valve is arranged between the water supply source and the germ reduction connection and is designed to be fully closed thus preventing the ingress of germ-reducing fluid into the water supply source. By means of such a water system it is possible to carry out sterilization or disinfection very easily and quickly without this requiring any major maintenance work.

Abstract: Systems and methods for fluid transfer between a first vessel and a second vessel that are separated by a body of water. The systems and methods may include extending a deployed portion of a fluid conduit assembly between the first vessel and the second vessel. The fluid conduit assembly includes a fluid conduit and also may include a fluid conduit support; and, in the deployed portion, the fluid conduit may be suspended from and supported by the fluid conduit support. The systems and methods also may include the use of a conformation control assembly to automatically and/or dynamically adjust the length of the deployed portion to regulate a conformation of the deployed portion.

Abstract: The aircraft includes: a fuel tank panel; a fuel pump bell, the bell being fastened to the panel; and a metal support arranged so that the bell is fastened to the panel entirely via the support.

Abstract: A system for transfer of crude oil from a production platform to a tethered barge is provided, comprising one or more hose reels which include swivels to facilitate connection/flanging while the hoses are being deployed into the water or retracted. The reels employ a semi-closed design which helps to contain spills. A floating hose is employed to eliminate the need for buoys or floats which must be attached to the hose as it is being deployed from the reel, or detached as the hose is retracted back onto the reel. A buoy is also used on either side of a KLAW device for connecting the hoses. The KLAW device includes shut-off ball valves on either side, and the KLAW device is adapted to separate when a predetermined level of tension is reached on the hose segments it connects.

Abstract: The invention provides a refuel valve assembly 240 for refuelling a first and a second fuel tank on an aircraft, wherein the refuel valve assembly 240 comprises an inlet for receiving fuel from an orifice 215 in a structure 213 of the aircraft, a first 251a and a second outlet 251b for delivering fuel from behind the structure to the first 211a and second 211b fuel tanks, and a refuel control apparatus for controlling fuel flow to the first and second outlets; wherein the refuel control apparatus includes a controllable valve assembly, so that delivery of fuel through the first outlet to a first fuel tank can be controlled independently of delivery through the second outlet of fuel to a second fuel tank. The invention also provides a method of refuelling a first and a second fuel tank on an aircraft.

Abstract: An annular seal for use in a fluid conveyance system that is subject to a high voltage event includes a center core having a generally tubular shape, the core having a circumferentially projected cross-section that is defined by inner and outer core radial surfaces, and core axial surfaces that are opposite one another. The sidewalls each have a generally tubular shape and a circumferentially projected cross-section that is defined by inner and outer sidewall radial surfaces, and first and second sidewall axial surfaces that are opposite one another. The first sidewall is attached along one of its axial surfaces to one of the core axial surfaces, and the second sidewall is attached along one of its axial surfaces to the other of the core axial surfaces. The center core has an electrical resistance that is less than an electrical resistance of each of the first and second sidewalls.

Abstract: A system for simulating wet runway conditions by using a liquid container that is placed inside an aircraft. The liquid container is connected to a nozzle that sprays water in front of the wheels of the aircraft. A valve is used to control the flow of water from the nozzle. Systems, such as the braking system of the aircraft, can then be tested in wet runway conditions simulated by the system. The amount of water sprayed from the nozzle can also be electronically controlled in relation to the speed of the aircraft, such that the nozzle sprays a nearly uniform layer of liquid in front of the wheels. The system can also be modified to include two tanks to manipulate the center of gravity of the aircraft.

Abstract: A smart drain valve comprises a support plate, a bolt passing through a center of the support plate, an outer plate connected to a first end of the bolt, an inner plate connected to a second end of the bolt, and a spring positioned between the inner plate and the support plate. The spring is made of a shape memory material.

Abstract: A draining apparatus for draining liquids from a vehicle includes a containment; a drain mast having an outlet opening and an inlet; and an actuator. The containment is adapted for being coupled with a structure of the vehicle, wherein the actuator is coupled with the drain mast and adapted for moving the drain mast into a retracted position and at least one extracted position relative to the containment, and wherein the containment is further adapted for accommodating the drain mast in the retracted position at least partially. The drainage apparatus has clear advantages regarding the parasitic drag compared to known drainage masts as it is only deployed into the flow when it is absolutely necessary.

Abstract: A pressure supply system for a fresh water system is provided. The pressure supply system includes a water reservoir having a bleed air inlet and a water outlet. The pressure supply system also includes a water pump so as to load water, which is loaded with bleed air pressure, with a further pressure downstream until a predetermined nominal operating pressure range is achieved. As a result, the pressure supply system provides an increased redundancy by pressure generator assemblies which are based on different pressure generation principles.

Abstract: A water supply system includes a first pipe, a water reservoir, and a Venturi pipe having a first Venturi nozzle terminal, a second Venturi nozzle terminal and a Venturi nozzle branch arranged between the first and second Venturi nozzle terminal. The first Venturi nozzle terminal is connected via the first pipe to the water reservoir. The first Venturi nozzle terminal is connectable to a second pipe to fill the water reservoir. The branch of the Venturi pipe is connectable to a third pipe to supply taps. Water flows through the Venturi pipe from the first Venturi nozzle terminal to the second Venturi nozzle terminal when the water reservoir is filled, and water flows through the Venturi pipe from the second Venturi nozzle terminal to the Venturi nozzle branch during the supply procedure, to provide a water supply system which requires less maintenance and is less temperamental.

Abstract: A device for the protection against the rupture of pipes carrying a fluid includes two or more flow channels and a closing element which interrupts the flow of fluid if a predetermined permissible volume flow is exceeded. At least one of the flow channels can be closed by a test closure in order to increase the flow speed in the remaining flow channels and for test purposes to bring about a movement of the closing element into the closing position. In this way, devices for the protection against the rupture of pipes integrated into complex systems carrying a fluid can be tested in situ to verify their proper functioning.

Abstract: A shower system for use in aircraft while in flight, the shower system having a feed line through which a stream of water can be supplied to the shower system; a showerhead from which a prepared stream of shower water can exit the shower system and a water stream parameter modification device for modifying at least one parameter of the water stream, said water stream parameter modification device incorporated between the feed line and the showerhead, wherein the water stream parameter modification device comprises at least one valve, which opens when not exposed to any pressure upstream to enable an evacuation of the entire shower system.

Abstract: The aircraft comprises: a fuel valve; an actuator for controlling the valve; and a tank panel extending between the valve and the actuator. It is arranged in such a manner that the bearing point(s) between the panel and a first one of the members selected from the valve and the actuator, and preferably the actuator, is/are provided by means of the second one of these members.

Abstract: A bleed valve module for mounting to a support structure within an aircraft includes a pipe, a plurality of bleed valves connected to the pipe, a plurality of pneumatic actuators connected to the plurality of bleed valves, and a vibration isolating element. The pipe contains a flow of bleed air and includes a plurality of inlets and an outlet. The plurality of bleed valves controls the flow of bleed air in the pipe. The plurality of pneumatic actuators actuate the plurality of bleed valves. The vibration isolating element connects the bleed valve module to the support structure within the aircraft and isolates the bleed valve module from vibration.

Abstract: Aircraft architecture, aircraft trolley, aircraft monument, aircraft water supply unit and aircraft having a hybrid water/waste system architecture having a combined decentralized and centralized water supply and waste system. In one example, the aircraft architecture comprises a plurality of toilet units each having a waste water terminal. At least one of the plurality of toilet unit comprises a local flush system, and the flush system has a receptacle for a replaceable flush fluid container. The waste water terminal of each of the plurality of toilet units is connectable to a centralized waste water system of an aircraft.

Abstract: The aircraft emergency oxygen supply system includes one or more sources of supplemental breathable oxygen, one or more inlet valves for one or more breathing devices, connected to the inlet valves, and one or more cabin air pressure transducers. A pressure controller controls the inlet valves in response to the one or more cabin air pressure transducers. One or more second pressure transducers may connected to conduits downstream of inlet valves to be monitored, and the pressure controller may also control operation of the inlet valves in response to the one or more second pressure transducers.

Abstract: A multiple process service vessel including a first module configured to mix drilling fluids and a second module configured to remediate drilling waste, wherein the first and second modules are located at least partially below the deck of the vessel. A method of processing drilling components, the method including transferring a first drilling fluid component from a pressurized vessel on a multiple process service vessel to a mixing unit at a first location; mixing the first drilling fluid component with a second drilling fluid component in the mixing unit to produce a drilling fluid; transferring the drilling fluid to a second pressurized vessel; moving the multiple process service vessel to a second location; and transferring the drilling fluid from the second pressurized vessel to a drilling location.

Abstract: A system and method to mitigate the effect of hydrodynamic ram. The system including a chamber adapted to receive fluid and a core disposed within the chamber. A plurality of columns extend through the core and a plurality of orifices extend through the thickness of the columns. The method includes channeling a portion of a vapor bubble to an ullage space disposed within the chamber with the plurality of columns and changing the fluid state of the vapor bubble with a plurality of orifices extending through the thickness of the plurality of columns.

Abstract: An aircraft cabin pressure control system outflow valve includes a frame, a valve element, and a vortex generator structure. The vortex generator structure is coupled to the valve element and is rotatable therewith, and includes a plurality of first vortex generators and a plurality of second vortex generators. The first vortex generators spaced are apart from each other and are configured to generate first vortices when the valve element is in an open position and fluid flows through the flow passage. The second vortex generators are formed in each of the first vortex generators and are spaced apart from each other. The second vortex generators are each configured to generate second vortices, which are smaller than the first vortices, when the valve element is in an open position and fluid flows through the flow passage.

Abstract: The oil recovery system minimizes environmental contamination and oil leakage into the ocean in the event of a rupture of the hull of an oil tanker. The oil recovery system includes at least one buoyant reservoir for receiving recovered oil, which is deployed into the ocean upon detection of a breach or rupture in the hull of the oil tanker. At least one conduit is in fluid communication between at least one oil tank housed within the oil tanker and the at least one buoyant reservoir. Upon detection of an oil spill from the oil tanker, the at least one buoyant reservoir is released from the hull of the oil tanker into the water and oil from the at least one oil tank is routed to the at least one buoyant reservoir to minimize the size of the oil spill.

Abstract: A method for transferring fluids between a first ship, called a barge, and a second ship, called a shuttle, in which the shuttle is positioned at a pre-determined distance from the barge, and a flexible fluid transfer conduit is guided from the barge to the shuttle. The shuttle is placed in a position laterally offset from the barge and essentially parallel to the longitudinal axis of the barge, and a fluid transfer system enables the shuttle to move in the lateral and longitudinal directions in relation to the barge, during a transfer. The invention is useful for the transfer of liquefied natural gas.

Abstract: A flow body is disclosed, particularly for aircraft. The flow body includes an outer side impinged on in a predetermined manner by a fluid in a direction of impinging flow, the flow body having on its outer side at least one flow control device including micro-perforations arranged in at least one segment of the outer side, at least one connecting passage communicated with the micro-perforations via at least one suction chamber so fluid flowing through the micro-perforations flows via the suction chamber into the connecting passage, at least one suction device having a first inlet communicated with the connecting passage, a second inlet communicated with at least one ram fluid feed line, wherein the ram fluid feed line is in a region of the flow body opposite to the direction of impinging flow of the flow body, and an outlet device for discharging the fluid.

Abstract: A system for efficiently transporting hydrogen from where it can be economically made to where it is most needed using specially designed airships. Technologies such as geothermal, wind, solar, wave tidal or hydropower can be used to generate electricity in-situ or very near to the primary energy sources. This electricity can then be used to produce hydrogen directly from water through various methods known in the art. Hydrogen can be delivered from the place where it is produced to the place where it is needed using an airship in which the hydrogen gas can also be used for generating lift, providing propulsion energy and serving ancillary needs. In other embodiments of the invention, the airship of the present invention can be used to dramatically reduce the cost of transportation of freight, the cost of passenger transportation, and to save on the area required for landing at the points of loading/unloading and embarkation/debarkation.

Abstract: A mount structure for a two-way valve for a fuel tank of a small boat for improving mountability of the two-way valve while ensuring strength of the deck. The interior space of the boat, which is formed of a hull and a deck, is provided with an engine, a fuel tank, and a duct. One end of the duct is attached to the wall surface of the deck with a mount member. The two-way valve is connected to the breather hose of the fuel tank, and attached to the mount member at one end of the duct from the interior space of the boat. The mount member is integrally provided with a mount pipe for the tube which opens the two-way valve outside the deck.

Abstract: A detachable surface flow enhancement device is provided, comprising: an aerodynamic structure configured to deflect moving air incident upon the aerodynamic structure; and an attaching element configured to attach the aerodynamic structure to a surface of a vehicle and to detach he aerodynamic structure from the surface of the vehicle without altering the surface of the vehicle.

Abstract: A negative pressure valve assembly is provided. The valve assembly comprises a valve port assembly comprising a port and a flange substantially surrounding the port, a valve comprising a plate adapted to substantially cover the port, the plate comprising a minor edge, a major edge having a major edge length, and a plate biasing assembly stop located at a first position along the major edge, the first position more than 50% of the major edge length as measured from the minor edge. The valve assembly further comprises a hinge coupled to the plate, the hinge adapted to couple the plate to the flange, and first plate biasing assembly adapted to couple to the valve port assembly and to bias the plate towards the valve port assembly, the first plate biasing assembly comprising a resilient member adapted to contact the stop plate.

Abstract: The invention relates to a device for receiving liquids in an aircraft and/or releasing liquids therefrom, especially during the flight, said device being arranged especially in an airplane. The aim of the invention is to provide a device which can receive large quantities of liquids in a rapid, reliable and flexible manner. To this end, the device can include a tank module with at least one tank container that is connected to a collector using a connecting shaft and a bulkhead module that can be connected to the tank module by the collecting tank. A closing element in the open position releases liquid from the tank module. In addition, a refueling module which is connected to the tank module by a supply line and a tube arranged on a winding device, and a receiving element attached to the tube, can provide refueling of the device.

Abstract: An arrangement for transferring a fluid, such as liquefied natural gas, to a ship. The arrangement includes a manifold and a device for offsetting a manifold connector beyond an edge of the ship. The device includes a fixed tubular portion connected to the manifold and a mobile tubular portion, mobile between a transfer position, in which the device is connected to a fluid transfer duct, and a rest position, inside the ship. The mobile tubular portion is pivotably mounted between the rest and transfer positions and is connected to the fixed tubular portion in the transfer position, and separated from the fixed tubular portion in the rest position. The manifold connector of the fixed tubular portion is located so that axes of opening apertures of the fixed and mobile tubular portions coincide in the transfer position of the mobile tubular portion.

Abstract: A fluid check valve for use in an aircraft fluid handling system having a confined surrounding structure where a first distance is defined between a fluid duct and the surrounding structure where the design of the fluid check valve is configured to facilitate removal of a first flange and the flow duct by moving the first flange and flow duct a second distance that is less than the first distance. The check valve is offset into the upstream side of a second flange to provide the reduction in the distance that the first flange has to be displaced to remove the first flange and flow duct from the check valve. A first alternate configuration of the fluid check valve utilizes rotational stops attached to the downstream surface of the flow flaps and in a second alternate embodiment configuration, rotational stops extend upstream from the flow flaps and make contact with at least one tower structure to limit the flow flap rotation in the open position.

Abstract: An aircraft having a dihedral wing configuration with a wing fuel tank and a vent system for ventilating the fuel tank, the vent system comprising: a combined vent-surge tank disposed inboard of at least part of the wing fuel tank; a vent fluidically connecting the combined vent-surge tank to ambient; and a vent line fluidically connecting the upper part of the fuel tank to the combined vent-surge tank, wherein the vent line has its lowest point at the combined vent-surge tank.

Abstract: The invention relates to a device (1) for receiving liquids in an aircraft and/or releasing liquids therefrom, especially during the flight, said device being arranged especially in an airplane. The aim of the invention is to provide a device which can receive large quantities of liquids in a rapid, reliable and flexible manner.

Abstract: An enhanced aerial delivery system addresses issues raised when large quantities of fluids, powders, and other agent materials are to be transported in and aerially dispersed by aircraft. Some aspects include positioning and securing of tanks aboard the aircraft to facilitate management and safety of the tanks and aircraft. Other aspects address coupling of the tanks and associated piping to lessen structural effects upon the aircraft. Further aspects deal with channeling, containing, and dumping stray agent materials that have escaped from the agent tanks on board the aircraft.

Abstract: An aircraft (10) having a cabin (14) with a plurality of potable-water-using stations (22) that drain graywater to a transfer tank (24). The graywater ejection system pressurizes the transfer tank (24) at appropriate times and/or places, so that graywater can be ejected through a drainmast (26) without the help of gravity. This graywater ejection system eliminates the need for a discharge line from the transfer tank (24) and frees the aircraft's fuselage (12) from having an inconvenient port associated with such a discharge line.

Abstract: The present invention relates to an arrangement of line connections for installations in an aircraft passenger cabin. The arrangement comprises a line connection element for accommodating several line connections; wherein the line connection element has a fixed position in the floor grid; wherein the line connections are adaptable to system lines of aircraft systems; and wherein the installations are adaptable by way of flexible inlet lines on the line connection element.

Abstract: A valve for use in aircraft comprises a body, a selective interrupter positioned inside the body for rotation therein, a flow arrangement between the selective interrupter and the body, a bonnet connected to the body and in contact with the selective interrupter, an arm extending through the bonnet and connected to the selective interrupter, and an actuator movably connected to the arm.

Abstract: An actuator control system has a dual concentric servo valve having a spool and at least one motor adapted to selectively displace the spool.

Abstract: System for transport of untreated drill cuttings, comprising a tank (2). The tank (2) is arranged below the deck of a ship (1) and has an output unit (10) at the bottom (6), to feed the drill cuttings towards an output opening (8). A pump (21) is provided below the bottom of the tank (2) to feed the drill cuttings through an unloading line (13). The unloading line (13) has a substantially uniform cross section and is shaped so that the velocity of the flow close to the inner wall is substantially equal in the same cross section. The tank (2) has an upper circular cylindrical part (3) and a lower frustuconical part (4) and a substantially flat bottom (6). In the flat bottom (6) is an output opening (8), which extends from the side wall (5) of the frustuconical part (4) to an inner dome or cone (11).

Abstract: An enhanced aerial delivery system addresses issues raised when large quantities of fluids, powders, and other agent materials are to be transported in and aerially dispersed by aircraft. Some aspects include positioning and securing of tanks aboard the aircraft to facilitate management and safety of the tanks and aircraft. Other aspects address coupling of the tanks and associated piping to lessen structural effects upon the aircraft. Further aspects deal with channeling, containing, and dumping stray agent materials that have escaped from the agent tanks on board the aircraft.

Abstract: An aircraft cabin pressure control system outflow valve includes a frame, a valve element, and a position sensor. The frame is configured to be mounted on an aircraft exterior skin. The valve element is rotationally coupled to the frame, and is coupled to receive an actuation drive force. The valve element is responsive to the actuation drive force to rotate to a position between a closed position and a plurality of open positions. The position sensor is coupled to the frame and is configured to directly sense rotation of the valve element and supply a position signal representative of valve element position.

Abstract: A method and apparatus for aerial fire suppression utilizing a potable fire retardant chemical dispensing system, readily adaptable, without extensive aircraft modification, to various makes of aircraft, for dispensing current types of forest and range fire fighting chemicals. The aerial delivery system is self contained and reusable. It enables cargo/utility aircraft to carry and dump a load, under control. The aerial delivery system is capable of attachment at the wing box, pressurized delivery from the nozzles, and nozzles directed straight downward.