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Matches 251 - 300 out of 1,011

Document Document Title
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.  
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 ...  
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...  
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...  
WO/2009/098012A4
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...  
WO/2009/130690A3
A pylon device (10) for suspending a payload (12) beneath an aircraft wing or fuselage. The device comprises a main body with a top surface (22) to face the aircraft and a bottom surface for engaging with the payload. At least one pneuma...  
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...  
WO/2009/100897A8
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...  
WO/2009/068807A3
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...  
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...  
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...  
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.  
WO/2009/098012A3
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...  
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...  
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...  
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...  
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 ...  
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 ...  
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...  
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...  
WO/2009/046084A3
A method and apparatus for lighting protection. In one advantageous embodiment a method forms a lighting protection system on a composite surface of an aircraft. A dielectric coating is formed on the composite surface in which the dielec...  
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...  
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...  
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 ...  
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...  
WO/2008/070946A3
Aircraft fuel tanks, systems and methods increase an aircraft's fuel capacity. The fuel tanks have a tank body defining an interior space for holding aircraft fuel, and a relief manifold assembly operatively associated to the tank body t...  
WO/2005/065071A3
An aircraft (100) designed for transonic speed comprises an airfoil (102), a nacelle (122), an engine (116), and an inverted V-tail (114). The nacelle is mounted on the lower aerodynamic airfoil surface and behind the trailing edge of th...  
WO/2008/156933A9  
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...  
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...  
WO/2008/156933A2  
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...  
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...  
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...  
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...  
WO/2008/054521A3
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...  
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...  
WO/2008/063547A3
A fuel pickup may include a fuel pickup tube having a plurality of holes for receiving fuel from inside a fuel container. A wicking material may envelop at least one of the plurality of holes. Aircraft fuel systems including such a fuel ...  
WO/2008/070946A2
Aircraft fuel tanks, systems and methods increase an aircraft's fuel capacity. The fuel tanks have a tank body defining an interior space for holding aircraft fuel, and a relief manifold assembly operatively associated to the tank body t...  
WO/2008/059287A1
A fuel system comprising: a fuel line coupled to an engine; a fuel pump (20, 21) having an inlet coupled to a fuel tank (11) and an outlet coupled to the fuel line; and a water scavenging system having an inlet (32) for collecting water ...  
WO/2008/059288A1
A fuel pumping and water scavenging system for pumping fuel from a fuel tank towards an engine, the system comprising: first and second fuel pumps (20, 21) each having a pump inlet (22, 31) for collecting fuel from the fuel tank; and a w...  
WO/2008/054521A2
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...  
WO/2008/048267A1
A fuel system for a mobile platform is provided. The system includes a crossfeed fuel transmission assembly (18) having a single crossfeed valve (46) that controls fuel consumption from a first fuel tank (26) and a second fuel tank (30) ...  
WO/2008/030097A1
The invention pertains to use of a low-temperature ozone conversion means containing an ozone catalyst composition supported on a honeycomb structure in cabin conditioning and/or inerting fuel tanks. The ozone conversion means preferably...  
WO/2008/011217A3
Fluid sensing systems and methods, including sensors used to sense various fluid levels in vehicles, are disclosed herein. One aspect of the invention is directed toward a method for sensing a fluid that includes passing electromagnetic ...  
WO/2008/022965A1
The present invention essentially relates to an aircraft comprising a fuselage (2) with a cockpit (4) for receiving passengers and/or a load and a propulsion system, said propulsion system comprising at least a tank (6) and/or a combusti...  
WO/2008/011217A2
Fluid sensing systems and methods, including sensors used to sense various fluid levels in vehicles, are disclosed herein. One aspect of the invention is directed toward a method for sensing a fluid that includes passing electromagnetic ...  
WO/2008/000923A1
The present invention relates to an anti-slosh device (D) of a flexible tank (21), provided with an upper cushion (22) as well as a lower base (23) and a plurality of sides (24), comprises at least one first (1) and one second (2) attach...  
WO/2008/000854A1
An electrical insulating system for a line element that forms part of a fluid system subjected to risks of possible external electrical discharges, such as the fuel system of an aircraft. Use is made of an insulating insert (12) between ...  
WO/2007/128953A1
An aircraft wiring installation connecting a set of fuel side wires in an aircraft fuel tank to a set of airside wires outside the fuel tank, the installation comprising: a connector box having a fuel side wall (22) and an airside wall (...  

Matches 251 - 300 out of 1,011