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WO/2011/085933A3 |
The invention relates to a tank for a cryogenic liquid gas, in particular for LNG; that is, for liquid natural gas or liquid methane. The invention further relates to an aircraft having such a tank and to a method for producing such a ta...
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WO/2011/162876A3 |
There is provided a method for mitigating static discharge in a fuel container (26). The method provides a static dissipative coating having a volume resistivity of 1.0x109 Ω-m (ohm-meter) or less when measured at 40 V (volts) or less, ...
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WO/2012/057039A1 |
A pipe support structure for an aircraft is provided with: a translation mechanism for supporting a pipe so that the pipe can be translated; and an angle adjustment mechanism for supporting the pipe so that the angle thereof can be adjus...
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WO/2012/056076A1 |
The invention relates to filler panels for aircraft fuel tank coveringings. The filler panels (45) cover the gaps between the upper and lower coverings (19, 21), stiffened by stringers (25, 25', 25"), of an airfoil of an aircraft structu...
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WO/2012/045031A1 |
An aircraft system (5) is disclosed including: a fuel storage system (10) comprising a first fuel tank (21) capable of storing a first fuel (11) and a second fuel tank (22) capable of storing a second fuel (12); a fuel cell system (400) ...
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WO/2012/013957A1 |
The invention provides a refuel control system for controlling refuel of at least one tank (111,112,113, 14,115,116) onanaircraft100,the refuel control system comprising monitoring apparatus (241, 242, 280, 371, 372, 380, 311, 312, 313, ...
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WO/2012/013351A1 |
To save weight und to enhance safety, a hydrogen tank 18 for supplying an engine 12 with hydrogen is attached externally to an aircraft 10.
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WO/2011/135135A3 |
The invention relates to a device (1) for installing a conducting component (2) on a structure (3) made of compound material, the inside of said structure (3) including a starter substance, that includes an installation element (4) on wh...
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WO/2011/006953A3 |
Methods and apparatus are disclosed for preventing or reducing occurrence of free water in an aircraft fuel tank operating in use within predetermined temperature and pressure ranges. Each of these includes the step of controlling the co...
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WO/2011/150967A1 |
The aircraft refuelling equipment (20) of an aircraft comprises a pipework (22) in which a fuel supply line (13) is connected to a plurality of tank supply lines, fuel tanks connected to tank supply lines of the pipework, first valves (2...
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WO/2011/109842A3 |
The invention relates to a tank (1) for holding an operating agent for a vehicle, comprising a substantially cylindrical metal casing (2) which is sealed at least at one end by an end cover (3) or end container (4) consisting of injectio...
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WO/2011/120939A3 |
A method of fuelling an aircraft for a flight to a predetermined destination in which the aircraft is loaded, the actual zero fuel weight of the loaded aircraft is determined, the fuel requirement of the loaded aircraft for that destinat...
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WO/2011/120939A2 |
A method of fuelling an aircraft for a flight to a predetermined destination in which the aircraft is loaded, the actual zero fuel weight of the loaded aircraft is determined, the fuel requirement of the loaded aircraft for that destinat...
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WO/2011/117610A1 |
A fuel system comprising a fuel tank (1), a vent tank (3) having a duct open to the ambient atmosphere, a first vent line (4, 5) fluidically connecting the fuel tank ullage to the vent tank (3), a gas drying system (8) including a pump (...
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WO/2011/110881A1 |
The invention relates to a fuel tank. The fuel tank is provided with an elastic partition which corresponds to the fuel tank in circumference and shape. The tank is divided into two chambers, a fuel chamber (10) and an excess fuel chambe...
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WO/2011/064519A3 |
The invention relates to an aircraft comprising a structural element, such as a fuselage, a wing or a tail unit, including: a wall separating the inside and the outside of the element and including portions jointly defining an inner volu...
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WO/2011/037855A3 |
An aerial vehicle is configured to operate in a base fuel cell operating mode and a fuel cell boost operating mode. A method for controlling the aerial includes providing a base fuel cell upper power limit. The method further includes co...
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WO/2011/037850A3 |
A method for managing power flow within an aerial vehicle includes determining a fuel cell power limit and a battery energy reserve. The method further includes determining a flight operation power requirement. The method further include...
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WO/2011/068443A1 |
The invention relates to helicopters with removable fuel tanks, wherein all fuel tanks of the helicopter are removable fuel tanks. Helicopters all fuel tanks of which are removable can safely be stored on ships and aircraft carriers.
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WO/2011/064519A2 |
The invention relates to an aircraft comprising a structural element, such as a fuselage, a wing or a tail unit, including: a wall separating the inside and the outside of the element and including portions jointly defining an inner volu...
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WO/2011/051210A1 |
The invention relates to a fuel cell system having a device for drying gases, comprising at least one cooling body having at least one first surface and at least one removal device. The cooling body is designed to be thermally connected ...
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WO/2011/026965A3 |
The invention relates to a mobile tank for a cryogenic, that is to say supercooled propellant or fuel, specifically in particular for LNG, that is to say liquid natural gas or liquid methane. The invention also relates to an aircraft hav...
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WO/2011/042215A1 |
The invention relates to a cooling system for cooling a fuel cell system (2) in a vehicle and for thermally connecting to fuel (8) in a fuel tank. This results in the fuel (8) in a fuel tank (6) being used as a heat sink having high ther...
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WO/2011/037850A2 |
A method for managing power flow within an aerial vehicle includes determining a fuel cell power limit and a battery energy reserve. The method further includes determining a flight operation power requirement. The method further include...
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WO/2011/037855A2 |
An aerial vehicle is configured to operate in a base fuel cell operating mode and a fuel cell boost operating mode. A method for controlling the aerial includes providing a base fuel cell upper power limit. The method further includes co...
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WO/2010/119105A3 |
The invention relates to a device for preventing the passage of gases and/or liquids exiting from an aircraft wingbox (2) into an aircraft fuselage located therebelow. According to the invention, the device comprises at least one sheet m...
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WO/2011/010124A1 |
An aircraft fuel tank ventilation system, comprising a refrigerative dehumidifying device (17) having a refrigerating element (21) in contact with air flowing between a vent (15) open to the atmosphere and a fuel tank (4, 5). Also, a met...
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WO/2011/010123A1 |
An aircraft fuel tank ventilation system comprising a dehumidifying device (17) disposed in flow communication between a vent (15) open to the atmosphere and a fuel tank (4,5). Also, a method of dehumidifying air introduced into an aircr...
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WO/2011/006953A2 |
Methods and apparatus are disclosed for preventing or reducing occurrence of free water in an aircraft fuel tank operating in use within predetermined temperature and pressure ranges. Each of these includes the step of controlling the co...
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WO/2011/004119A1 |
The invention relates to a device (6) for closing a fuel-dump circuit (48) of an aircraft, including a coupling tip (43). The tip has a seal (31) and a means (34) for changing a dimension (d) of the seal.
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WO/2010/103305A3 |
A fuel system comprising a liquid fuel tank, an engine, and a cyclonic separator (1) having an inlet (2) fluidically connected to the fuel tank, a first outlet fluidically connected to an engine fuel feed system, and a second outlet (4)....
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WO/2010/104379A3 |
The invention relates to an inflatable element for use interiorly in a fuel tank of a vehicle, vessel or aeroplane, wherein the inflatable element is provided with means, by which inflating gas is supplied into or discharged from the inf...
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WO/2010/119105A2 |
The invention relates to a device for preventing the passage of gases and/or fluids exiting from a wingbox (2) of an aircraft into an aircraft fuselage located therebelow. According to the invention, the device comprises at least one she...
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WO/2010/113793A1 |
Provided is a fuel tank for an aircraft, the fuel tank capable of suppressing electrostatic charge, for example, caused by flow electrification with fuel. Specifically, a fuel tank for an aircraft is provided with an upper outer plate (5...
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WO/2010/113640A1 |
Disclosed is a composite tank that can curb static buildup, corrosion, and strength degradation. Also disclosed are a wing provided with said composite tank and a method for manufacturing the composite tank. The composite tank is charact...
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WO/2010/104379A2 |
The invention relates to an inflatable element for use interiorly in a fuel tank of a vehicle, vessel or aeroplane, wherein the inflatable element is provided with means, by which inflating gas is supplied into or discharged from the inf...
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WO/2010/098243A1 |
A fuel-tank ignition prevention structure is provided with double layered sleeves passed through a hole formed in a rib, and also with a support structure for supporting a pipe passed through the double layered sleeves. The support struc...
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WO/2010/097492A1 |
The invention relates to a drain valve attachment system. Drain valves are used to extract the water that accumulates in the lower part of the fuel tanks of aircraft and are attached at a lower coating that forms part of the tanks. The l...
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WO/2010/086677A1 |
The ejectable tanks are fuel tanks with less fuel capacity, compare to the ones used actually, they can be launched from the airplane in case of an emergency to prevent fire or explosion, without loosing the full capacity of fuel.
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WO/2009/141400A4 |
The invention relates to an inerting system for an aircraft, comprising at least one air separation module provided with at least one air inlet, a first air outlet and a second air outlet. Said air separation module is designed in such a...
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WO/2010/064463A1 |
A fuel tank of aircraft capable of suppressing the occurrence of spark on a pipe by the flow of a lightning current therethrough at a lightning strike and of suppressing the charging of a pipe with static electricity due to flow charge w...
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WO/2010/061155A1 |
A method of operating an aircraft fuel management system for an aircraft having at least one fuel tank, each fuel tank having an associated fuel quantity indicator arranged to provide an indication of the amount of fuel in the associated...
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WO/2010/058147A1 |
A fuel monitoring system for automatically monitoring a fuel transfer in an aircraft fuel system, the fuel system including a plurality of fuel tanks (2, 4, 6, 10, 12), the fuel monitoring system comprises a fuel quantity sensor (14) arr...
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WO/2009/141400A3 |
The invention relates to an inerting system for an aircraft, comprising at least one air separation module provided with at least one air inlet, a first air outlet and a second air outlet. Said air separation module is designed in such a...
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WO/2010/037677A1 |
A safety system for reducing the explosion risk of a fuel tank has at least one fluid source and at least one fluid container (10) having an inlet (22) and an outlet (24) for a fluid, wherein the fluid container (10) has a structure that...
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WO/2010/038052A1 |
An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mou...
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WO/2009/139801A3 |
A fuel system for an aircraft includes a fuel collector downstream of a boost pump and upstream of an engine fuel pump.
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WO/2009/092146A3 |
Auxiliary fuel tanks are provided with an inner barrier wall defining an interior volume for containing aircraft fuel, an outer barrier wall adjacent the inner barrier wall so as to define a space therebetween, and a drain part having a ...
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WO/2008/086587A3 |
An Auxiliary Fuel Tank (TCA - 'Tanque de Combustivel Auxiliar') inside an aircraft is described, the TCA having a convex shape light constructive structure formed by an internal hull I that constitutes a first barrier, and by an external...
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WO/2010/001238A1 |
The present application is directed to dielectric isolators for use in aircraft fuel systems to control lightning induced current and allow dissipation of electrostatic charge. The dielectric isolators are configured to have a high enoug...
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