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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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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...
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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 ...
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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...
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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) ...
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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...
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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...
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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 ...
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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...
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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 ...
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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 (...
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WO/2007/121551A1 |
A method of pre-heating a liquid in an aircraft reservoir (30) to facilitate pumping of the liquid during a cold start, the method comprising providing an electric motor (34), a pump (32) and a controller (42), the electric motor being c...
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WO/2007/074177A1 |
The invention relates to an electric insulation device for a linear element which forms part of a fuel system that is at risk of possible external electric discharges. The inventive device is formed by a part (13) which is made from an i...
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WO/2007/071932A1 |
Some water drain valves tend to fill with water which may freeze, thereby jamming the valve. This invention provides an aircraft water drain valve (1) comprising a passageway (11), a shaft (9), a first sealing member (13) and a second se...
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WO/2007/071908A1 |
An aircraft fuel tank assembly (101) includes a tank for holding fuel (102), a canister (111) and a fuel pump assembly (103). The fuel pump assembly (103) includes: an electric motor (104), a pump (105) and an electronics unit (106). The...
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WO/2007/071909A1 |
One or more main aircraft fuel tanks (34) are provided with one or more fuel gauges (42) arranged to provide a measure of the amount of fuel in said one or more main fuel tanks. One or more auxiliary fuel tanks (30) are also provided. Th...
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WO/2007/053931A1 |
The gas turbine engine 10 comprises at least one electrical generator 30, 32 and an electrical heater 34, 26 associated with a gas path of the engine 10. The heater 34, 36 is powered by the generator 30, 32 to selectively add heat to the...
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WO/2007/039650A1 |
The invention relates to a method of protecting a group of metal devices (13, 15) which are disposed inside a fuel tank (11) that is made wholly or partially from composite materials, such as a tank housed in an aircraft, against electri...
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WO2006126162B1 |
The invention relates to filling elements for shafts, tanks, tank vehicles, containers and pipe lines, in order to deviate heat, and/or to increase cell-type distribution of the volume chamber ( Quenching ), in order to prevent and surpr...
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WO/2007/017184A1 |
The present invention pertains to a tank module for an aircraft. The tank module is designed for being fitted into the aircraft fuselage from outside. The tank module (1) comprises at least one receptacle (10) and a shell section (5) tha...
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WO/2007/008185A2 |
Method and arrangement for dispersing fuel (62) within a fuel containment system (60) of an aircraft (30) including utilizing a fuel containment system on an aircraft that is located at least partially within a wing (34) of the aircraft ...
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WO/2006/136736A2 |
The invention relates to a method for detecting and localising a fuel leakage in the engine of a multi-engine aircraft consisting in (a) determining a fuel consumption (L240, L244) for each aircraft engine, (b) in comparing the consumpti...
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WO/2006/124745A2 |
A fuel distributor (10) and mounting arrangement that helps support the weight of the fuel distributor (10) during removal and replacement for improved maintainability. The mounting arrangement includes a hanger (60) mountable on a first...
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WO/2006/111108A1 |
A receptacle (10) for storing a liquid comprises a device (11, 12) for feeding one or more substances that render the liquid thixotropic to the liquid in the receptacle (10). The invention is characterized in that the device (11, 12) is ...
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WO/2006/104427A1 |
The invention relates to an aircraft gas-dividing and gas-distributing system comprising an oxygen/nitrogen generator which is connected to an air-conditioning system through the inlet line thereof and to a fuel tank pressurisation syste...
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WO/2006/087486A1 |
The invention relates to a system for inerting a compartment of a vehicle, typically a fuel tank (1) for supplying the gas turbine (3) of an aircraft with fuel. Said system comprises a filtering device (5) arranged between the compressed...
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WO/2006/079782A2 |
A method and system for inerting an aircraft fuel tank is disclosed. A gas separation module (18) is provided comprising a plurality of strands of hollow fibre separation membrane wound around a core. Cabin air (17) is drawn through the ...
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WO/2006/058774A2 |
A supply system (100) for the energy supply in an aircraft comprising an engine (101) for propelling an aircraft, a fuel cell (102) for supplying an aircraft with electric energy, a first fuel reservoir (103) for supplying the engine (10...
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WO/2006/058603A2 |
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WO/2006/049956A1 |
A dielectric tubular fitting (210; 500; 150; 370; 210') for dissipating electrical energy, while providing fluid flow therethrough, the fitting (210; 500; 150; 370; 210') including coaxial first (176; 176'; 224; 224'; 214L, 214R) and sec...
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WO/2006/018226A1 |
Nowadays in aircraft on-board inert gas generation systems (OBIGGS) are used to generate inert gases. Cooled bleed air of engines or auxiliary turbines is fed to said OBIGGS systems. According to an embodiment of the present invention, a...
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WO/2006/018225A1 |
Nowadays in aircraft so-called on-board inert gas generation systems (OBIGGS) are used to generate inert gases, to which OBIGGS cooled bleed air of engines or auxiliary power units is fed. According to an embodiment of the present invent...
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WO/2006/020286A2 |
An on-board inert gas generating system (10) includes a flow control valve (28) modulated according to changes in ambient conditions to minimize changes to oxygen content within a fuel tank (18). The quality of the nitrogen-enriched air ...
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WO/2006/016853A1 |
A maintenance unit (10) for facilitating maintenance of an aircraft comprising a housing air driven equipment said equipment including a fuel vapour purging device (75) and operator breathing apparatus (25) wherein the equipment are moun...
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WO/2006/015456A1 |
Eco protective impenetrable universal reservoir made of waved (zigzagged) ballistic Kevlar for airplanes, tanker and other vehicles, which is installed by the paneling of tanker (1) or by the wing casing or hull. He is protracting inside...
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WO/2006/013346A1 |
Unsafe electric energies can exist in aircraft fuel tanks as a result of static build-up or induced currents from lightning strikes. The invention provides an aircraft having a ground circuit (19) and including a fuel tank (1) having a f...
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WO/2006/013351A1 |
Unsafe electric energies can exist in aircraft fuel tanks as a result of static build-up or induced currents from lightning strikes. The invention provides an aircraft fuel tank (1) including two discharge paths (18-21-5 & 18-20-15-16-17...
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WO2005097599A9 |
A method and apparatus for defueling an aircraft. The apparatus includes a defueling fitting comprising one or more structural connectors, which may include one or more suction cups. The one or more structural members are attached to a m...
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WO/2005/118073A2 |
An inert gas generating system (50) for generating inert gas on a vehicle having a fuel tank (66) and a fuel tank vent (68). The system includes an inlet (70) for receiving a flow of gas having a nitrogen component and an oxygen componen...
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WO/2005/115123A2 |
An inerting system (10) for an aircraft (12) includes one or more fuel tank circuits (15) associated with fuel tanks (16). An air source (17) supplies pressurized air. A heat exchanger (56) cools the pressurized air. An air separation mo...
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WO/2005/106306A1 |
The present invention relates to spacers and pipelines. The spacers 4,10 are mounted between two pipes 1,3 - an internal line and an external line - and hold them at a defined distance. A closure 6 is necessary for fixing the spacer on t...
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WO/2005/084156A2 |
Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft...
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WO/2005/082712A1 |
An inerting system for an aircraft fuel tank (10) uses an air separation device (12) to produce a supply of nitrogen-enriched air to replenish the fuel tank on consumption of fuel and to maintain the pressure difference across the walls ...
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WO/2005/076822A2 |
The waste disposal service panel assembly includes a housing, waste drain valve, rinse/fill valve, handle assembly and service panel door. The housing has a tubular side wall and a base near one end of the side wall. The waste drain valv...
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WO/2005/063362A1 |
A gas separation module (25) is disclosed for separating air into nitrogen (27) and oxygen (26) enriched fractions. The nitrogen enriched fraction 27 may be used to inert an atmosphere inside a fuel tank (32). The air is separated into n...
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WO/2005/021377A1 |
This invention makes the atmosphere inside of the aircrafts’ fuel-tank non-explosive by suppressing the formation of the fumes/vapor of aviation fuel due to the discharged-heat of the air-conditioner of the passenger cabin. This invent...
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