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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/2011/120939A2 |
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/2011/068443A1 |
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/2011/042215A1 |
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/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/2010/119105A2 |
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/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/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/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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WO/2009/147456A1 |
The "Fuel Deposit" consists of bags (F,F,H) of moderate sizes, with qualities like resistance, flexibility, and others, which will make impossible to spill its content, to catch fire or explode if the content is fuel. They should be prov...
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WO/2009/141400A2 |
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/2009/137942A1 |
An auxiliary fuel tank system connected to a main tank of an aircraft having a refuel input assembly. The auxiliary fuel tank system comprises an ejector system operatively connected to the refuel input assembly, a forward tank operative...
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WO/2009/139801A2 |
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/2009/100897A1 |
The invention relates to a system (10) for ventilating an explosive region (12) of an aircraft, comprising a ram air channel (16), which has an air inlet for supplying ambient air into the ram air channel (16), and an air outlet (18). Th...
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WO/2009/098012A2 |
An aircraft tank system (10) comprises a tank cell for housing fuel, a fuel line (12), connecting the tank cell to fuel inlet connector (14) and a venting device (16), which connects the tank cell to the environment for venting. A shut-o...
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WO/2009/096939A1 |
A fuel jettison system which provides pilot-initiated automatic operation to jettison fuel down to a 60 minute useable fuel remaining level while the manual operation, requiring the pilot to hold down the jettison panel switch, jettisons...
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WO/2009/092146A2 |
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/2009/091632A1 |
In accordance with the present invention, there are provided simplified systems and methods for catalytically deactivating, removing, or reducing the levels of reactive component(s) from the vapor phase of fuel storage tanks. The simple ...
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WO/2009/074597A1 |
The invention relates to an integrated device (1) for the protection against electrical discharges of conductive fixing elements between one another or of a conductive fixing element and another conductive element of aircraft, comprising...
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WO/2009/068065A1 |
An apparatus (10) for testing an aircraft tank system (12) comprises a fuel supply device (14) including a fuel reservoir (16), a fuel supply line (18) for supplying fuel from the fuel reservoir (16) to a fuel outlet (20) of the fuel sup...
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WO/2009/068807A2 |
The invention relates to a method for controlling the thermal effluents of an aircraft including an airframe (110) and at least one propulsion unit (112), wherein said at least one propulsion unit (112) includes a turbomachine (116) supp...
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WO/2009/063060A1 |
The invention relates to a device (1) for the protection against electrical discharges of a conductive fixing element (4) of an aircraft, comprising a cap (2) made of non-conductive material and a washer (3) made ofnon-conductive materia...
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WO/2009/063063A1 |
The invention relates to a device (12) for protecting a conductive fixing element (5) of an aircraft subjected to high charges against electrical discharges, the device (12) comprising a cap (6) made of non-conductive material, a washer ...
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WO/2009/050510A1 |
A tank forcontaining a fluid, such as fuel, oil or gas within a chamber (7). The walls ofthe chamber are partially defined by a rigid structure havinganopening,- and partially defined by an elastomeric diaphragm (8) which is attached aro...
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WO/2008/156933A9 |
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WO/2009/016299A2 |
A fuel line valve (1) for an aircraft, that comprises a shell (13) capable of rotation inside the valve body (16) and connected to a driving shaft (14) driven by an electric actuator (11). The valve further includes a torque generation m...
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WO/2009/007614A2 |
The invention relates to a method for the maintenance of an aircraft tank (10) including a flexible bladder (12) provided in a chamber (14) formed in the structure (16) of said aircraft, an interstitial gap (20) being provided between sa...
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WO/2008/134161A1 |
Apparatus and methods are provided to minimize the escape of fuel out of a fuel tank (14) when a tank wall is penetrated by a bullet. In one embodiment, a pressure differential may be maintained between a pressure (32) within a fuel tank...
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WO2008054521B1 |
Hydrogen powered air vehicles (100) that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 18288m (60,000 ft) carrying pay loads of up to 907,2kg (2,000 pounds). Embodiments may include features suc...
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WO/2008/110837A1 |
A water scavenging system (1) for removing water from an aircraft fuel tank (2), the water scavenging system comprising: a water line (10); and a valve (20) which is configured to control the flow of water in the water line in response t...
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WO/2008/110838A1 |
A method of removing water (7) from a fuel tank (2) using a water scavenging line (4) which has an inlet (6) immersed in the water and an outlet (5) coupled to a water tank (3). The method comprises filling the fuel tank with fuel (30) w...
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WO/2008/086587A2 |
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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