| Class / Patent application number | Description | Number of patent applications / Date published |
|---|
| 244135000 | Flexible containers | 9 |
| 20080223988 | System For Inerting a Compartment of a self-Propelled Vehicle, Especially an Aircraft - The invention relates to a system for inerting a compartment of a vehicle, typically a fuel tank ( | 09-18-2008 |
| 20080230654 | HYDROGEN FUELED BLENDED WING BODY RING TANK - A toroidal shaped or ring fuel tank located within the loft line of a blended wing body aircraft is disclosed. The ring tank may be used in an aircraft to store liquid hydrogen fuel with a reduced tank weight. The ring tank may be continuous with no tank end domes typically found on cylindrical pressure tanks, reducing tank weight for a given fuel volume. The ring tank configuration avoids increasing the aerodynamic shape of the aircraft and does not encroach on usable passenger or payload areas of the aircraft. In one example the ring tank may be configured in a nose down position such that the forward portion of the ring tank is outside the pressurized cabin area. | 09-25-2008 |
| 20080272237 | Aircraft Auxiliary Fuel Tank System and Method - One or more main aircraft fuel tanks are provided with one or more fuel gauges arranged to provide a measure of the amount of fuel in said one or more main fuel tanks. One or more auxiliary fuel tanks are also provided. The aircraft uses fuel during a first phase of fuel consumption, upon commencement of which phase the auxiliary fuel tanks hold fuel. After the first phase said one or more auxiliary fuel tanks are empty and a second phase commences. During the first phase, an indication of the amount of fuel carried by the aircraft is provided by means of summing (i) the amount of fuel in the main fuel tanks as measured by said one or more fuel gauges and (ii) the amount of fuel remaining in said one or more auxiliary fuel tanks as calculated using a measure relating to the fuel consumption rate. During the second phase of fuel consumption, an indication of the amount of fuel carried by the aircraft is provided on the basis of the amount of fuel measured by said one or more fuel gauges. | 11-06-2008 |
| 20080290219 | Method and apparatus for treating fuel to temporarily reduce its combustibility - A method and apparatus are disclosed for treating fuel to temporarily reduce its combustibility, and thereafter restore its combustibility. As used in an aircraft, the method comprises the following steps:
| 11-27-2008 |
| 20080315038 | Fuel Tank Valve - Some water drain valves tend to fill with water which may freeze, thereby jamming the valve. This invention provides an aircraft water drain valve comprising a passageway, a shaft, a first sealing member and a second sealing member. The shaft is moveable between an open position in which the first and second sealing members are arranged to allow free passage of fluid through the passageway, and a closed position in which both the first and second sealing members are arranged to prevent free passage of fluid through the passageway thereby preventing ingress of fluid into the region between the first and second sealing members. Thus water may be hindered from collecting and freezing in the part of the valve close to the cold wall of the fuel tank. | 12-25-2008 |
| 20090189021 | AUXILIARY AIRCRAFT FUEL TANKS, SYSTEMS AND METHODS PROVIDING VISUAL LEAK DETECTION - 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 port in fluid communication with the space to allow leaked fuel within the space to be discharged therefrom. The drain part may be positioned at a corner junction between at least side and bottom walls of the outer barrier wall. In some advantageous embodiments, the drain part is positioned at a corner junction between the side wall, the bottom wall and an end wall of the outer barrier wall. One or more drain parts may be provided on each auxiliary aircraft fuel tank. If a plurality of drain parts are provided, then each drain part will preferably have a port in fluid communication with the space between the inner and outer barrier walls to allow leaked fuel within the space to be discharged therefrom, and each drain part will be positioned at respective corner junctions between at least side and bottom walls of the outer barrier wall, preferably between the side wall, the bottom wall and an end wall of the outer barrier wall. Aircraft may thus be provided with one or more of such auxiliary fuel tanks. | 07-30-2009 |
| 20090212162 | AIRCRAFT WINGS AND FUEL TANKS - On failure, a burst rotor of a wing-mounted engine ( | 08-27-2009 |
| 20090302163 | OXYGEN EXCHANGE MANIFOLD, SYSTEMS AND METHODS FOR INERTING A VOLATILE ENVIRONMENT - An oxygen exchange manifold converts oxygenate air into an oxygen depleted air stream for use in inerting an otherwise flammable environment. A system including the oxygen exchange manifold may be utilized to inert fuel tanks of an aircraft or another environment. Methods of inerting such environments are also disclosed. | 12-10-2009 |
| 20090321577 | PROTECTIVE DEVICES FOR AIRCRAFT FUEL FILLER PORTS - Protective devices are provided subjacent to the filler port within an aircraft's wing fuel tank so as to protect the lower wing skin from being struck by a nozzle associated with refueling equipment. The protective devices for an aircraft fuel filler port may be associated with an aircraft wing tank and preferably include a generally cylindrical side wall structure and a hemispherical bottom apertured wall joined to an annular bottom edge of the side wall. The hemispherical bottom apertured wall may include a screen mesh, but apertured hemispherical cup-shaped members may also be employed and achieve equivalent benefits. | 12-31-2009 |
| 20100051749 | AIRCRAFT SPILLOVER FUEL TANK - Apparatus and methods described herein provide for a spillover tank to extend the fuel capacity of the main wing tank of an aircraft. The spillover tank is located in the wing of the aircraft adjacent to the main wing tank. At least one aperture exists through the shared barrier between the main wing tank and the spillover tank that allows fuel to flow passively between the tanks. A scavenge pump mechanism driven by motive flow from the main fuel pumps continuously pumps fuel from the spillover tank into the main wing tank. | 03-04-2010 |
| 20100116941 | Ducting for a fuel pipeline of aircraft or spacecraft, method for producing same and aircraft wing incorporating same - The present invention relates to a ducting for a fuel pipeline of an aircraft or spacecraft, in particular designed to be mounted in each of the wings of an aircraft, an aircraft wing incorporating this ducting and a method for producing same. | 05-13-2010 |
| 20100140411 | Fuel supply unit for a fuel cell system, fuel cell system and method for monitoring a fuel supply unit - A fuel supply unit ( | 06-10-2010 |
| 20100176244 | Intelligent Ballistic Parachute System with Fuel Discharge - A method performed by an aircraft, the aircraft including a wing, aircraft fuel, and a whole-aircraft parachute that is coupled to the aircraft. The method comprises: deploying the whole-aircraft parachute while the aircraft is in flight; and after deploying the parachute, but before the aircraft contacts the earth or any object coupled to the earth, discharging at least a portion of the aircraft fuel from the wing of the aircraft. | 07-15-2010 |
| 20100176245 | CROSS SHIP ARCHITECTURE FOR DISPATCH CRITICAL FUEL TANK INERTING SYSTEM - A fuel tank inerting system uses two “half systems” for providing inerting gas for the fuel tanks. Each inerting system may be composed of a temperature control and air pressurization unit (TCPU) and an air separation unit (ASU). A cross-ship duct and valve allows using one TCPU (sized for about half capacity or more, but less than full system capacity) connected to two ASUs. The inerting system may provide for redundancy in the TCPU section. | 07-15-2010 |
| 20100264274 | EDGE SEAL FOR FIBRE-REINFORCED COMPOSITE STRUCTURE - A fibre-reinforced composite structure includes a cut edge; an elastomeric cap covering the cut edge; and an adhesive sealant bonding the elastomeric cap to the cut edge. The fibre-reinforced composite structure is joined to a component and the elastomeric cap includes a generally Z or L-shaped cap with a web bonded to the cut edge of the fibre-reinforced structure and a flange bonded to the component and extending away from the fibre-reinforced structure. | 10-21-2010 |
| 20100288883 | Method for detecting a fuel leakage in an aircraft engine and system for carrying out said method - A method for detecting and localizing a fuel leakage in the engine of a multi-engine aircraft consisting in determining a fuel consumption for each aircraft engine, in comparing the consumption of each engine with the other aircraft engines, in determining the engine exhibiting the greater fuel consumption ratio, in determining the excess consumption ratio of the aforementioned engine with respect to the other engines, in checking whether the excessive consumption is caused by a leakage and in triggering an alarm if the step is checked. A system for detecting and localizing a fuel leakage in the engine of a multi-engine aircraft including an airborne computer for carrying out the aforementioned method is also disclosed. | 11-18-2010 |
| 20110062288 | INERTING SYSTEM FOR AN AIRCRAFT - The invention pertains to an inerting system for an aircraft featuring at least one air separation module with at least one air inlet, a first air outlet and a second air outlet. The air separation module is designed for splitting an input air flow into a first air flow and a second air flow, wherein the first air flow is enriched with oxygen in comparison with the input air flow and discharged at the first air outlet and the second air flow is enriched with nitrogen in comparison with the input air flow and discharged at the second air outlet. In comparison with known inerting systems, the inerting system according to the invention is characterized in that the air inlet can be connected to an air extraction point in an air processing system and the inerting system is designed for routing the first air flow into a cabin to be air-conditioned. | 03-17-2011 |
| 20110068231 | NEA DISTRIBUTION SYSTEM FOR OBIGGS APPLICATIONS - A method for creating ullage in a fuel tank includes the steps of porting NEA into a mixing chamber during descent, exposing the mixing chamber to ambient air and communicating a mixture of NEA and ambient air into the fuel tank. A complementary apparatus to the method includes a mixing chamber for receiving NEA during descent, a port for communicating ambient air with the mixing chamber during descent and a port for communicating a mixture of the NEA and the ambient to the fuel tank. | 03-24-2011 |
| 20110101166 | CONTROL UNIT AND METHOD FOR CONTROLLING THE SUPPLY OF A VEHICLE WITH MULTIPLE FUELS - A control unit for controlling the supply of a vehicle having at least one internal combustion engine with multiple fuels has at least one input means for supplying optimization parameters, fuel parameters, and operational data, at least one storage unit for storing the optimization parameters, the fuel parameters, and the operational data, and at least one computing unit. The control unit is adapted for being connected to at least one first supply apparatus for supplying a first fuel to the internal combustion engine and to at least one second supply apparatus for supplying a second fuel to the internal combustion engine, and of controlling a first mass flow of supplied first fuel and a second mass flow of supplied second fuel. The computing unit optimizes the ratio of first mass flow and second mass flow for all operational phases of the vehicle to fulfill the specified optimization parameters. | 05-05-2011 |
| 20110168845 | AIRCRAFT SKIN PANEL WITH ULTRASONIC GAUGE - 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 mounted to an inner surface of the skin layer adjacent to the hole in the skin layer; and an access panel which covers the hole and can be removed to gain access to the gauge. | 07-14-2011 |
| 20110180667 | TETHER ENERGY SUPPLY SYSTEM - A tether continuous energy supply system for an unmanned aerial vehicle comprising: a ground station, a ground station energy system, a spool coupled to the ground station energy system at a rotating joint, a tether that is wound about the spool, wherein a first end of the tether is coupled to the rotating joint, a tension control motor coupled to both the spool and the ground station energy system, an unmanned aerial vehicle coupled to a second end of the tether, a UAV energy system, a fluid that moves throughout the tether continuous energy supply system, a tension control system that receives and transmits signals from a plurality of sensors contained within the tether continuous energy supply system, and a distributed controls system that receives and transmits signals from the plurality of sensors contained within the tether continuous energy supply system. | 07-28-2011 |
| 20110284694 | AIRCRAFT FUEL TANK - An aircraft fuel tank that is capable of suppressing the occurrence of sparks on a pipe caused by a lightning current through the pipe during a lightning strike, and also suppressing static electricity charging of a pipe caused by flow electrification generated by the fuel. An aircraft fuel tank ( | 11-24-2011 |
| 20110290943 | METHOD AND APPARATUS FOR COOLING FUEL IN AN AIRCRAFT FUEL TANK - Fuel in an aircraft fuselage fuel tank is cooled by means of cold air flowing from the exterior of the aircraft to a cooling region inside the aircraft. The cooling region may be (a) located to the exterior of the fuel tank, (b) in thermal communication with the fuel tank and (c) in fluid communication with a region downstream of, and remote from, said cooling region, for example, an exhaust port on the outside of the aircraft. The flow of air may be caused by air entering a ram air intake, into which air passes as a result of the motion of the airborne aircraft relative to the surrounding air. | 12-01-2011 |
| 20110297790 | AIRCRAFT FUEL TANK - An aircraft fuel tank capable of suppressing electrostatic charging caused, for example, by flow electrification with the fuel. The aircraft fuel tank comprises an upper skin ( | 12-08-2011 |
| 20120006943 | AIRCRAFT INCLUDING A FUEL PUMP FASTENED TO A TANK PANEL - The aircraft includes:
| 01-12-2012 |
| 20120012710 | COMPOSITE TANK, WING, AND METHOD FOR MANUFACTURING COMPOSITE TANK - A composite tank that can suppress electrification, corrosion and strength degradation, a wing comprising the composite tank, and a method for manufacturing the composite tank. The composite tank comprises: a tank body inside which a combustible material is stored, having a first resin portion ( | 01-19-2012 |
| 20120025026 | Venting gas from a tank - The present invention provides a tank vent device for venting gas from a tank | 02-02-2012 |
| 20120037758 | METHOD AND APPARATUS FOR TREATING FUEL TO TEMPORARILY REDUCE ITS COMBUSTIBILITY - A method and apparatus are disclosed for treating fuel to temporarily reduce its combustibility, and thereafter restore its combustibility. As used in an aircraft, the method comprises the following steps:
| 02-16-2012 |
| 20120104172 | Fuel Line in an Aircraft - A line segment of a fuel line in an aircraft for connecting at least three lines is provided. In order to provide fuel channeling in an aircraft, having, for example, better damage or leakage features, a line segment is provided that has a wall structure forming a continuous cavity. The wall structure has at least three adapter openings for connecting the continuous cavity with respectively one line. The wall structure is designed double walled between the adapter openings in such a way that an intermediate cavity is formed, which encases the continuous cavity. | 05-03-2012 |
| 20120104173 | DEVICE FOR SHUTTING A JETTISONING CIRCUIT OF AN AIRCRAFT - A device for shutting an aircraft jettisoning circuit includes a coupling endpiece. The endpiece carries a sealing gasket and means suitable for modifying a dimension of the gasket. | 05-03-2012 |
| 20120119032 | SECOND HOSE WALL - Embodiments of the present invention provide second wall hoses for use in a fuel system in order to ensure that, in the event of failure of the first internal hose, the second wall hose contains any leakage. Specific embodiments are designed for particular use on aircraft, where weight is sought to be kept as minimal as possible. | 05-17-2012 |
| 20120193479 | AIRCRAFT FUEL SYSTEM - An aircraft fuel system has a fuel tank with first and second cells separated by one or more baffles. A venting system reduces pressure difference between the interior and exterior of the fuel tank, and an inerting system supplies oxygen-depleted gas to the fuel tank. The baffles permit the flow of fluid between the cells. The venting system has one or more vent nozzles within the fuel tank and in fluid communication with one or more vent ports. The inerting system has one or more inerting nozzles for injecting oxygen-depleted gas into the first and second cells. A control device varies the ratio between the total flow rates of the oxygen-depleted gas into the first and second cells. | 08-02-2012 |
| 20120248251 | CONDUIT PROTECTION SYSTEM AND METHOD - A conduit protection system, comprising: a conduit for carrying a fluid; a sealed vessel surrounding the conduit along a protected zone of the conduit; and a valve moveable between a first position for obstructing fluid flow through the protected zone of the conduit and a second position for enabling fluid flow through the protected zone of the conduit, wherein the valve is biased to the first position, and wherein the valve is fluidically coupled to the sealed vessel such that a positive pressure within the sealed vessel is operable to move the valve to the second position against the bias. Also, a method for protecting a fluid carrying conduit. | 10-04-2012 |
| 20120248252 | COOLING SYSTEM FOR FUEL CELL SYSTEMS, METHOD FOR COOLING FUEL CELL SYSTEMS, AND A FUEL CELL SYSTEM - A cooling system for cooling a fuel cell system in a vehicle is used for thermal connection with fuel in a fuel tank. This results in the use of the fuel in a fuel tank as a heat sink with a high thermal capacity and an essentially constant cooling capacity due to the relatively stable temperature of the fuel. Cooling of the fuel cell system can thus be implemented with very simple means and in a particularly lightweight manner. | 10-04-2012 |
| 20120305712 | Systems and methods for using an endothermic fuel with a high heat sink capacity for aircraft waste heat rejection - Systems and methods for rejecting waste heat generated by one or more operating systems installed on an aircraft employ an endothermic fuel that can participate in endothermic catalytic cracking at temperatures below about 80° C. when exposed to a cracking catalyst that contains a superacid operative to induce low-temperature catalytic cracking of the branched alkanes. The endothermic fuel contains an effective amount of the branched alkanes so that a net endothermic effect is realized when the fuel is exposed to the cracking catalyst. The low-temperature, heat-consuming cracking of the branched alkanes increases the heat sink capacity of the endothermic fuel. | 12-06-2012 |
| 20130001363 | FILLER PANELS FOR THE SKINS OF AIRCRAFT FUEL TANKS - An aircraft lifting surface structured as a torsion box comprising upper and lower skins ( | 01-03-2013 |
| 20130001364 | HELICOPTER WITH REMOVABLE FUEL TANK - Helicopters with removable fuel tanks Each fuel tank is a removable fuel tank. Each fuel tank is removable and can safely be stored on ships and aircraft carriers. | 01-03-2013 |
| 20130032672 | FUEL DELIVERY SYSTEM AND METHOD - A vehicle fuel delivery system for liquid fueled vehicles including a vehicle housing a pressure vessel for receiving, discharging and containing fuel. The vehicle fuel delivery system includes fuel lines for communicating fuel to the pressure vessel, and fuel lines for communicating fuel from the pressure vessel to a fuel delivery device. The vehicle fuel delivery system always maintaining positive fuel pressure throughout the delivery system. | 02-07-2013 |
| 20130200216 | SUPPLY SYSTEM FOR A MEANS OF A TRANSPORT, METHOD FOR PROVIDING AN INERT GAS AND ELECTRIC POWER, AIRCRAFT WITH SUCH A SUPPLY SYSTEM AND USE OF A FUEL CELL - The invention relates to a device for producing an inert gas that comprises a fuel tank for a fuel, at least one fuel cell with a cathode, an anode, a reactor for reforming fuel from the fuel tank into a hydrogenous fuel gas and an inert gas outlet. The reactor comprises a fuel gas outlet that is connected to a fuel gas inlet arranged on the anode of the fuel cell. The inert gas outlet is arranged downstream of the reactor and forms a fluid sink for non-hydrogenous reaction products of the reactor. | 08-08-2013 |
| 20130306797 | HYDROGEN TANK FOR H2-INJECTION - To save weight and to enhance safety, a hydrogen tank for supplying an engine with hydrogen is attached externally to an aircraft. | 11-21-2013 |
| 20130320147 | GEAR PUMP, PUMPING APPARATUS INCLUDING THE SAME, AND AIRCRAFT FUEL SYSTEM INCLUDING GEAR PUMP - A pumping apparatus includes a gear pump in fluid communication with a boost pump. The gear pump includes a pump housing, a first gear, and a second gear. The first and second gear have gear teeth and trunnions on opposite sides thereof, and are disposed in the pump housing. The gear teeth of the first and second gear are meshed in a mesh region. An inlet cavity is defined adjacent to the first and second gear, on one side of the mesh region. A pump outlet is defined on an opposite side of the mesh region from the inlet cavity. A bearing is configured to support at least one trunnion of the first gear and/or the second gear. A bearing interface is defined between the bearing and the at least one trunnion. A flow path is defined between the bearing interface and the inlet cavity. | 12-05-2013 |
| 20130320148 | IMPELLER, CENTRIFUGAL PUMP INCLUDING THE SAME, AND AIRCRAFT FUEL SYSTEM INCLUDING THE CENTRIFUGAL PUMP - An impeller, a centrifugal pump, and an aircraft fuel system are provided. The impeller includes a central hub disposed along a rotational axis of the impeller and that defines an axial bore extending through at least a portion of the central hub along the rotational axis. The central hub further defines an opening to the axial bore at a leading end of the central hub. The impeller further includes an impeller section spaced from the leading end and that includes at least one impeller vane fixed to the central hub. The impeller further includes an inducer section that is disposed between the leading end of the central hub and the impeller section and that includes at least one inducer vane extending along an outer surface of the central hub. The central hub defines at least one radial aperture in the inducer section in fluid communication with the axial bore. | 12-05-2013 |
| 20130320149 | SUPPORT FOR ROUTING CONDUITS IN AN AIRCRAFT WING - A routing support ( | 12-05-2013 |
| 20140014777 | OPTICAL LIQUID LEVEL SENSOR - An optical level sensor ( | 01-16-2014 |
| 20140117163 | CRYOGENIC TANK - A cryogenic tank includes a shell having an interior side, an exterior side, and an internal volume that is bounded by the interior side. The shell has a shape that includes at least two elongated lobes that are defined by partial cylinders that intersect each other. The partial cylinders extend lengths along central longitudinal axes that are offset from each other. The lobes include opposite domes that extend at opposite ends of the length of the corresponding partial cylinder. The cryogenic tank includes an internal reinforcement frame having a web of elongate frame members extending within the internal volume. The frame members extend along the interior side of the shell such that lengths of the frame members extend along paths that follow the profile of the interior side of the shell. The internal reinforcement frame is configured to distribute loads exerted on the shell along at least three different directions. | 05-01-2014 |
| 20140175227 | FLUID SEPARATION ASSEMBLY AND METHOD - In an embodiment there is provided a fluid separation assembly. The assembly has a hollow fiber bundle with a plurality of hollow fiber membranes. The assembly further has a first tubesheet and a second tubesheet encapsulating respective ends of the hollow fiber bundle, wherein one of the tubesheets has a plurality of radial through openings formed in the tubesheet. The assembly further has a housing surrounding the hollow fiber bundle and the first and second tubesheets, the housing having a feed inlet port, a permeate outlet port, and a non-permeate outlet port. The feed gas, permeate gas, or non-permeate gas are introduced into or removed from the hollow fiber membranes via the plurality of radial through openings formed in the tubesheet, such that the radial through openings of the tubesheet intersect each or substantially each of the hollow fiber membranes. | 06-26-2014 |
| 20140191085 | OUTER FUEL TANK ACCESS COVER, WING AND AIRCRAFT - An outer fuel access tank cover (FTAC) of an aircraft, a wing comprising such outer FTAC of an aircraft and an aircraft are provided. In one example, an outer fuel tank access cover (FTAC) ( | 07-10-2014 |
| 20140209749 | FUEL PRESSURE SENSOR LINE RESERVOIR - The present invention concerns a device for use in an aircraft fuel pressure sensor line. More particularly, but not exclusively, this invention concerns a fuel pressure sensor line connecting an aircraft fuel pump to a pressure sensor. The invention also concerns a fuel pressure sensor line reservoir for use with a sensor line connecting an aircraft fuel pump to a pressure sensor. An aircraft fuel pump system comprises an aircraft fuel pump and a pressure sensor connected the aircraft fuel pump via a sensor line. The sensor line includes a reservoir located between the aircraft fuel pump and the pressure sensor. The reservoir acts to prevent liquid contacting the pressure switch when the fuel pump is not active. | 07-31-2014 |
| 20140239122 | METHOD FOR SEALING A FUEL TANK - A method for making a structural element comprising a panel in composite material with fiber reinforcement in an organic matrix obtained by laying up and curing. The panel comprises a side likely to be exposed to contact with hydrocarbons. The required layer structure is obtained by laying up the plies of fibers pre-impregnated with resin having a curing temperature T1. A ply made of a thin film of polymer that can withstand hydrocarbons and the curing temperature T1, referred to as the protective film, is applied on the side exposed to hydrocarbons. The entire layered structure is cured under pressure at the temperature T1. | 08-28-2014 |
| 20140284426 | Joint Assembly to Form a Sealed Flow Conduit - An apparatus comprising an elongated structure, a first plate, and a second plate. The elongated structure has a channel. The elongated structure is configured to be associated with a primary structure on a first side of the primary structure. The first plate is configured to be connected to the primary structure at a joint and cover a portion of the elongated structure. The first plate is connected to the primary structure on the first side of the primary structure. The second plate is configured to be connected to the primary structure on a second side of the primary structure. | 09-25-2014 |
| 20140339367 | EFFICIENT LOW CARBON EMISSION AIRPLANE INTEGRATING JET FUEL AND CRYOGENIC FUEL SYSTEMS - A hybrid fuel airplane and methods are presented. A cryogenic fuel is transferred to an airplane propulsor from an airplane fuel system comprising a cryogenic fuel tank and a jet fuel tank. The cryogenic fuel tank conforms to an outer mold line and carries a cryogenic fuel, and is located in a portion of the airplane body while not extending beyond the outer mold line. The jet fuel tank carries a jet fuel and is located in an airplane wing, or an airplane body, or both. A dynamic aircraft load is born on the cryogenic fuel tank, and the airplane propulsor is operated using the cryogenic fuel to generate thrust for the hybrid fuel airplane. An aerodynamic lift is generated using the airplane wing coupled to the airplane body. | 11-20-2014 |
| 20150034768 | AIRCRAFT FUEL SYSTEM AND AIRCRAFT - The present invention ensures explosion-proof performance without increasing the capacity for supplying nitrogen-enriched air in an aircraft fuel system having a ventilation function. An aircraft fuel system includes: fuel tanks; an NEA supply system; a left ventilation channel extending from a ventilation duct to a fuselage and leading into the tanks; and a right ventilation channel extending from a ventilation duct to the fuselage and leading into the tanks. The tank leading to the channel and the tank leading to the channel are separated by a central wall. The tanks communicate with each other through a fuel path, which allows, of fuel and gas, only the fuel to pass through, and float valves. | 02-05-2015 |
| 20150041592 | FUEL TANK, MAIN WING, AIRCRAFT FUSELAGE, AIRCRAFT, AND MOBILE BODY - A fuel tank in which it is possible to reduce working hours or cost in a manufacturing process and prevent an increase in weight in, a main wing, an aircraft fuselage, an aircraft, and a mobile body. The fuel tank is provided with a structural member using carbon fiber reinforced plastic in which a reinforcing material includes carbon fibers and a matrix includes plastic, wherein the matrix has electrical conductivity applied thereto. Furthermore, a cut surface of the structural member, which is formed by cutting the structural member, may be exposed to the inside in which fuel is accommodated, of a fuel tank. | 02-12-2015 |
| 20150048210 | System And Method For Reduced Flammability Of An Aircraft Fuel System - Disclosed is a method for controlling the flammability of fuel vapors in an aircraft main fuel tank that is located in whole or in part in the fuselage contour. The method comprises a fuel system architecture and fuel consumption sequencing maintaining liquid fuel in said main tanks during all normal operations. Ceasing the withdrawal of fuel from the main tank when the fuel reaches a predetermined level thereby limiting the volume and flammability exposure time of the fuel vapor ullage. Once the predetermined level is met the fuel is supplied from wing tanks throughout the remainder of the mission. The predetermined main tank fuel level at which wing tank fuel begins to be consumed is determined by the aircraft flight reserves fuel volume stored in the main tank as well as the amount necessary to continuously submerge the main tank fuel pumps during the entire mission. | 02-19-2015 |
| 20150053820 | Line System for an Aircraft and Aircraft with a Line System - A line system for an aircraft comprises at least one double-walled fluid line with an outer line body, an inner line body arranged therein and at least one spacer. The outer line body and the inner line body are fluid-tight, wherein the inner line body is realized in one piece of a flexible material. The at least one spacer is arranged on at least one of the inner line body and the outer line body in order to space apart and/or electrically insulate the inner line body and the outer line body. | 02-26-2015 |
| 20150053821 | VENT FOR AN AIRCRAFT WING FUEL TANK - An aircraft fuel tank vent opening having a liquid separation nozzle, the liquid separation nozzle and the opening dimensioned such that migration across the liquid separation nozzle to the underside of a wing, of fuel escaping from the vent opening, is inhibited during normal operating conditions. | 02-26-2015 |
| 20150069184 | CRYOGENIC FUEL TANKS FOR USE IN AIRCRAFT STRUCTURES - Cryogenic fuels tanks for use in aircraft structures are disclosed herein. An example apparatus disclosed herein an airfoil-shaped structure disposed outboard of a fuselage of an aircraft. The example apparatus also includes a first cryogenic fuel tank disposed inside the airfoil-shaped structure. | 03-12-2015 |
| 20150122948 | AIRCRAFT FUEL TANK ARRANGEMENT - An aircraft fuel tank arrangement for the relief of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere is provided. The aircraft fuel tank arrangement comprises a removable cartridge received within a cartridge-receiving body located at least partially in the fuel tank, said cartridge comprising a first burstable member operable to rupture in the presence of a pressure differential between the interior of the aircraft fuel tank and the ambient atmosphere which is greater than a predetermined pressure differential. | 05-07-2015 |
| 20150307200 | TIME DOMAIN REFLECTOMETRY AIRCRAFT FUEL GAUGE - An aircraft fuel tank system comprising an aircraft fuel tank and a time domain reflectometry (TDR) fuel gauge for measuring a filling level of fuel in the aircraft fuel tank. The TDR fuel gauge comprises an electromagnetic signal generator and a cable, the cable comprising a first cable part and a second cable part which are coupled in series to the signal generator. The first cable part extends downwardly within the fuel tank and the second cable part extends upwardly within the fuel tank. The first and second cable parts are arranged such that for at least one filling level the first cable part extends down into the fuel from an ullage space at a first location and the second cable part extends up out of the fuel into an ullage space at a second location which is spaced apart from the first location. | 10-29-2015 |
| 20150353201 | AIRCRAFT SYSTEMS AND METHODS WITH INTEGRATED TANK INERTING AND POWER GENERATION - A system is provided for inerting a fuel tank of an aircraft. The system includes a first compressor fluidly coupled to the fuel tank for removing an air and fuel vapor mixture from an ullage of the fuel tank. The system further includes a fuel processor fluidly coupled to the first compressor and configured to receive the air and fuel vapor mixture and to generate hydrogen from the air and fuel vapor mixture. The system further includes a fuel cell fluidly coupled to the fuel processor and configured to receive the hydrogen as anode fuel to produce electricity. The system further includes a combustor fluidly coupled to the fuel cell and configured to combust the exhaust product to produce combustion gas, and a first heat exchanger fluidly coupled to the combustor and configured to cool the combustion gas into inerting gas for the fuel tank. | 12-10-2015 |
| 20150360791 | TANK RETAINER IN AN AIRCRAFT - The invention concerns a tank retainer for retaining a tank in the fuselage of an aircraft which includes, between the tank and a frame rigidly connected to the fuselage of the aircraft, a hinged retaining means and a fastening rod on which said hinged retaining means is mounted. Advantageously, the hinged retaining means is intended to be connected to a rear end of the tank and the fastening rod is suitable for being mounted on the frame rigidly connected to the fuselage of the aircraft and, preferably, the hinged retaining means comprises a ball joint. | 12-17-2015 |
| 20150360792 | DEVICE FOR RETAINING A TANK IN AN AIRCRAFT - The present invention relates to a device for mounting and supporting a generally cylindrical or tapered tank, having a main axis X, that includes a pair of first means for retaining the tank along a vertical axis Z on each of a first and second end of the tank, a second means for retaining the tank along a horizontal axis Y, perpendicular to the main axis, on the first end of the tank, and a third means for retaining in a ball-and-socket joint, the means being located around the vertical axis and connected to the second end of the tank. | 12-17-2015 |
| 20160009406 | AIRCRAFT FUEL SYSTEM | 01-14-2016 |
| 20160023774 | DUAL-STAGE GEAR PUMP WITH REDUCED PRESSURE RIPPLE - A fuel system includes a fuel gathering system in fluid communication with a fuel storage container, and a fluid pump assembly in fluid communication with the fuel gathering system. The fluid pump assembly includes a main gear pump stage and a first flow attenuator. A main driven gear is meshed with a main drive gear in a main pump conduit, and a main pump bearing assembly rotatably supports the main drive gear and the main driven gear. The first flow attenuator is disposed around the main pump conduit, and includes a substantially polygonal fluid opening. Edges of the opening are substantially aligned with an undercut bearing portion on at least one of an inlet side and an outlet side of the main pump conduit to define a non-round fluid boundary. | 01-28-2016 |
| 20160031545 | FUEL TANK, MAIN WINGS, AIRCRAFT FUSELAGE, AIRCRAFT, AND MOVING BODY - The purpose of the present invention is to provide a fuel tank, main wings, an aircraft fuselage, an aircraft, and a moving body, which enable working hours and costs involved in a manufacturing process to be reduced, and weight increases to be prevented. The fuel tank includes a structural member in which carbon fiber reinforced plastic (CFRP) is used, the carbon fiber reinforced plastic (CFRP) including a reinforcing material that includes carbon fibers and a matrix that includes plastic. The structural member is formed by laminating a conductive sheet between prepregs of the carbon fiber reinforced plastic (CFRP). In this case, a cut surface of the structural member formed by cutting the structural member may be exposed on the inside in which fuel is stored. | 02-04-2016 |
| 20160039530 | AIRCRAFT FUEL TANK INERTING SYSTEMS - An aircraft fuel tank inerting system for a fixed wing aircraft having at least one main fuel tank in the wing and an associated surge tank includes a source of inerting fluid and a flow passage for supplying said inerting fluid to the main fuel tank and discharging it into the main filet tank through at least one discharge outlet. The flow passage includes a pressure relief arrangement adapted to discharge into the surge tank if a pressure in the main fuel tank exceeds a predetermined threshold. | 02-11-2016 |
| 20160176536 | FOOLPROOFING SYSTEM FOR PIPES BY MEANS OF AN OBSTACLE INSIDE A CONNECTOR IN AN AIRCRAFT DUCT | 06-23-2016 |
| 20080251643 | METHODS AND APPARATUS FOR RESISTING TORSIONAL LOADS IN AERIAL REFUELING BOOMS - A refueling boom for an aerial tanker includes an outer member operatively connected to the tanker, an inner member operatively and telescopically configured with the outer member, and one or more torque rollers. The torque roller is disposed on the outer member such that the torque roller engages with the inner member when the inner member is telescoping and reacts to torsional loads subject on the inner member when the boom is deployed in an aerial refueling operation. The inner member may include a plurality of longitudinally disposed torsion surfaces or races for respectively engaging with the torque rollers. | 10-16-2008 |
| 20080265097 | APPARATUS FOR AN AUTOMATED AERIAL REFUELING BOOM USING MULTIPLE TYPES OF SENSORS - A system for automated control of a refueling boom coupled to a tanker aircraft is provided. The system includes: a first inertial measurement unit (IMU) providing inertial measurements for the tanker aircraft; a first GPS receiver providing a GPS location for a GPS antenna attached to the tanker aircraft; and a processor adapted to calculate a first inertial navigation state for the tanker aircraft through integration of the inertial measurements, the processor being further adapted to calculate a first inertial navigation state error relative to the GPS location and to filter the first inertial navigation state error and the first inertial navigation state based upon noise characteristics of the first IMU and the first GPS receiver to provide an updated inertial navigation state for the tanker aircraft, the processor being further adapted to control the refueling boom relative to a receiver aircraft based upon the first and updated inertial navigation states. | 10-30-2008 |
| 20080302916 | SYSTEMS AND METHODS FOR AUTOMATICALLY AND SEMIAUTOMATICALLY CONTROLLING AIRCRAFT REFUELING - Aerial refueling systems and associated methods are disclosed. A system in accordance with one embodiment of the invention includes an operator input device configured to receive operator inputs and direct a first input signal corresponding to a target position for an aerial refueling device. A sensor can be positioned to detect a location of at least one of the aerial refueling device and a receiver aircraft, and can be configured to direct a second input signal. A controller can be operatively coupled to the operator input device and the sensor to receive the first and second input signals and direct a command signal to adjust the position of the aerial refueling device in response to both the first and second input signals, unless either or both of the input signals are absent or below a threshold value. Accordingly, the system can respond to both automatically generated sensor data and data input by an operator. A fully automated version of the system can be installed on an unmanned aircraft having additional capabilities, for example, electronic surveillance and/or jamming capabilities. | 12-11-2008 |
| 20080308679 | Device to reduce the lateral force generated by aerial refueling boom cross-section - Device to reduce the lateral force generated by an aerial refueling boom ( | 12-18-2008 |
| 20090032645 | AERIAL REFUELING SYSTEM - A method for operating an aircraft refueling system, where the aircraft refueling system has a computer system, a plurality of fuel tanks containing a fuel, a plurality of fuel pumps, a plurality of motor operated valves, and at least one refueling connection. The method may involve using the computer system to signal at least one of the motor operated valves to open; initiating a flow of the fuel to the at least one of the refueling connections using at least one of the pumps; sensing a flow condition of the fuel; signaling the flow condition to the computer system; and varying an operating quantity of the pumps in response to the flow condition. | 02-05-2009 |
| 20090039201 | Interoperable Aerial Refueling Methods - An Interoperable aerial refueling method enables tanker aircraft configured with a boom and receiver refueling system to refuel an aircraft configured for the probe and drogue refueling system. In one embodiment, a receptacle, coupled to a refueling drogue, is configured to fluidly receive a terminal portion of a refueling boom is. A retainer is coupled to an aircraft that removably retains the receptacle when the aircraft is refueling another aircraft configured to directly engage the boom. The receptacle releases the receptacle when the terminal portion of the boom engages the receptacle so that an aircraft that receives the refueling drogue may be refueled. | 02-12-2009 |
| 20090045290 | Method and system for inflight refueling of unmanned aerial vehicles - A system and method for refueling unmanned aerial vehicles. The system is adapted to refuel a first unmanned aerial vehicle from a second unmanned aerial vehicle and includes an arrangement for flying the first and second vehicles to proximity within a predetermined range and for connecting an umbilical from the second vehicle to the first vehicle in flight. In the illustrative embodiment, the arrangement for connecting includes a targeting system for electromagnetically detecting a refueling receptacle on the first vehicle. The targeting system includes a first coil around a refueling receptacle on the first vehicle. A seeker is disposed at a first end of said umbilical on the second vehicle. The seeker includes three detector coils adapted to detect a magnetic signal from the first coil around the receptacle on the first vehicle. The coils are mounted such that the detector coils point in different directions. The outputs of the coils are processed to determine the direction and range to the UAV from the tanker UAV. | 02-19-2009 |
| 20090050743 | Aircraft fuel tanks, systems and methods for increasing an aircraft's on-board fuel capacity - 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 to prevent an overpressure condition within the interior space of the fuel tank body. The relief manifold assembly preferably includes a buffer vessel defining a buffer chamber in fluid communication with the interior space defined by the fuel tank body. The buffer vessel may advantageously be fixed to the tank body within the interior space thereof. At least one of a fuel vent manifold assembly for venting the interior space of the fuel tank and a fuel refill/transfer manifold assembly for supplying fuel to and withdrawing fuel from the interior space of the fuel tank. At least one control box (e.g., containing valves, pumps and/or sensors) external of the fuel tank may be provided so as to fluid-connect the at least one fluid manifold assembly to the main fuel system of the aircraft. A plurality of aircraft fuel tanks may therefore be positioned adjacent to one another, preferably within the fuselage (e.g., a cargo compartment) of the aircraft so as to be disposed generally along a longitudinal axis of the aircraft. | 02-26-2009 |
| 20090095843 | ENHANCED RUDDEVATOR FOR IMPROVED AIR REFUELING BOOM FLIGHT CONTROL - In-flight fuel transfer from one aircraft to another aircraft or aerial refueling can extend the flight duration of a receiver aircraft and thereby increase its operational range and/or effectiveness by enabling it to fly farther or for longer duration without returning to the ground. Improved aerial fuel transfer is disclosed in connection with a method and system for in flight transfers of fuel from one aircraft to another. Enhanced fuel transfer operations including boom control are disclosed. | 04-16-2009 |
| 20090127394 | Refueling boom with backup raising cable - The invention relates to a backup device for raising a refueling boom ( | 05-21-2009 |
| 20090140099 | Device, method, and aircraft for illuminating in-flight operations - An device, method, and aircraft are provided for illuminating an in-flight operation, the device, method, and aircraft generating an electromagnetic radiation within the far-violet and ultraviolet spectrum, and thus being imperceptible to the naked eye, compatible with night vision equipment, and undetectable by night vision equipment. | 06-04-2009 |
| 20090184205 | METHOD AND APPARATUS FOR AERIAL FUEL TRANSFER - A method and apparatus for transferring fuel onto or off of an aircraft. A refueling transfer duct is deployed from an aft station of the aircraft being serviced while the aircraft is flying, wherein the transfer apparatus comprises a hose with a controllable drogue attached to its free end. The refueling duct is positioned through control signals sent by a tanker aircraft to the controllable drogue to form a favorably positioned refueling duct capable of a finite final docking maneuver. The positioned refueling duct is connected to the tanker aircraft positioned behind the aircraft to form a connection. The fuel is transferred through the connection to a fuel tank or fuel storage system located within the aircraft. | 07-23-2009 |
| 20090200426 | DROGUE DEPLOYING/RETRIEVAL DEVICE, SYSTEM, AND METHOD - An in-flight refueling device includes an arm, ring and actuator. The arm has a proximate end and a distal end. The ring is secured to the distal end and is configured to releasably secure a drogue for a refueling hose. The actuator is secured to the proximate end and is configured to extend the arm a predetermined distance. | 08-13-2009 |
| 20090230248 | USING A METALLOCENE TO REMOVE OXYGEN FROM A STREAM OF GAS - A filter includes a metallocene for removing oxygen from a gas stream. The filter further includes a support for the metallocene. | 09-17-2009 |
| 20090302160 | SYSTEM FOR REFUELLING OPERATIONS - System for hoisting and releasing an aircraft refuelling boom ( | 12-10-2009 |
| 20090302161 | Drogue Illumination - In a reception coupling and drogue assembly ( | 12-10-2009 |
| 20090302162 | PASSIVE VARIABLE SPEED DROGUE - The passive variable speed drogue includes an articulated center strut lever linkage assembly pivotally connected between adjacent pairs of center struts and trailing edge struts, biased by an extension spring mounted to the center strut to move the center strut to a required stop position to maintain substantially constant loads on the drogue within a range of refueling speeds, and to permit improved interfacing of the variable speed drogue assembly with a stowage tube. A center strut bumper on the center strut also provides improved interfacing of the variable speed drogue assembly with a stowage tube. | 12-10-2009 |
| 20100019090 | DROGUE ASSEMBLY FOR IN-FLIGHT REFUELLING - A drogue assembly includes a probe guide such as a standard small high speed drogue with a first canopy ( | 01-28-2010 |
| 20100025536 | Boom Force Absorber Systems and Methods for Aerial Refueling - Systems and methods for aerial refueling are disclosed. In one embodiment, an aerial refueling system includes a first conduit portion moveably coupled to a second conduit portion and moveable relative to the second conduit portion along a longitudinal axis, and a force absorbing assembly operatively coupled to the first and second conduit portions. The force absorbing assembly includes a first absorber portion and a second absorber portion engaged with the first absorber portion. The first absorber portion is configured to compress when subject to a compression force having a longitudinal component at least approximately aligned with the longitudinal axis, the longitudinal component tending to urge the first conduit portion toward the second conduit portion and causing absorption of at least a portion of the longitudinal component by the first absorber portion until the longitudinal component reaches a first limit. The second absorber portion is configured to compress when the longitudinal component exceeds the first limit. | 02-04-2010 |
| 20100072320 | PROGRAMMABLE AERIAL REFUELING RANGE - In an aerial refueling system for refueling a receiver aircraft in flight from a tanker aircraft, wherein the refueling system includes a hose reel rotatably coupled to the tanker aircraft's fuselage, a hose wound around the reel, said hose having an outlet end, and a drogue affixed to said outlet end, a hose reel drive system including a microprocessor electrically coupled to the reel; and a machine-readable program embodied in the microprocessor for directing operation of the system, the machine-readable program including instructions for establishing a refueling range. A method including receiving information of a receiver aircraft for aerial refueling; and establishing, in flight, a refueling range for an aerial refueling system coupled to a tanker aircraft based on the received information. | 03-25-2010 |
| 20100084511 | DEVICE, METHOD, AND AIRCRAFT FOR ILLUMINATING IN-FLIGHT OPERATIONS - An device, method, and aircraft are provided for illuminating an in-flight operation, the device, method, and aircraft generating an electromagnetic radiation within the far-violet and ultraviolet spectrum, and thus being imperceptible to the naked eye, compatible with night vision equipment, and undetectable by night vision equipment. | 04-08-2010 |
| 20100108815 | SELF CONTAINED POWER SYSTEM FOR CONTROLLABLE REFUELING DROGUES - According to an embodiment, an aerial refueling drogue has a coupling having a channel formed there through. One end of the coupling is attached to a hose. A power generator unit is positioned in the channel of the coupling. | 05-06-2010 |
| 20100108816 | INDICATION SYSTEM AND METHOD FOR REFUELLING OPERATIONS | 05-06-2010 |
| 20100163679 | OPTICAL TRACKING SYSTEM FOR AIRBORNE OBJECTS - An airborne tracking system including a radiation emitter, a radiation receiver and a signal processor. The radiation emitter is adapted to direct radiation to a positioning area a defined distance from the radiation emitter, the radiation carrying a modulated location signal containing information corresponding to positions within the positioning area. The radiation receiver is adapted to receive at least a portion of the emitted radiation carrying the modulated signal and output a signal to the signal processor indicative of the modulation of the location signal of the received radiation. Signal processor is adapted to process the outputted signal and identify a position within the positioning area indicative of the location in the positioning area of the received radiation. | 07-01-2010 |
| 20100213318 | CONDUCTIVE BODIES - An aircraft ( | 08-26-2010 |
| 20100237196 | ACTIVE STABILIZATION OF A REFUELING DROGUE - A refueling drogue adapted to connect to a refueling hose extending from a refueling aircraft. The drogue may include an active stabilization system adapted to effectively stabilize the refueling drogue via control surfaces on the refueling drogue when the refueling drogue is placed in an airstream. | 09-23-2010 |
| 20100243812 | METHOD AND DEVICE FOR IN-FLIGHT REFUELLING OPERATIONS USING A BOOM - Method and device for in-flight boom refuelling operations using an articulated boom ( | 09-30-2010 |
| 20100270431 | Aerial refuelling apparatus - A boom drogue adapter for a refuelling boom of an aerial refuelling apparatus comprises a linkage arm between the boom and a hose and drogue arrangement, which arm can be pivotally moved about the boom to adjust the position of the hose and drogue and take up hose slack. | 10-28-2010 |
| 20100282912 | POSITIONING SYSTEM FOR AERIAL REFUELING - A positioning system for aerial refueling of an aircraft provided with a first element for connection with a second element arranged on a tanker plane. The first and second elements are adapted to feed fuel from the tanker plane to the aircraft. A receiver on the aircraft is arranged to receive signals from the second element. A control unit on the aircraft controls the aircraft depending on the signals to steer the aircraft to a position for connecting the first and second elements. | 11-11-2010 |
| 20100282913 | Steerable Drogue - A steerable drogue ( | 11-11-2010 |
| 20100327116 | Smart boom tip assembly - A refueling apparatus for interconnecting a tanker aircraft ( | 12-30-2010 |
| 20110001011 | Assisted In-Flight Refuelling System - An assisted in-flight refuelling system having a tanker aircraft equipped with a drogue; a fuel take-on aircraft equipped with a probe; and a drogue-probe coupling assist system designed to determine a first distance between the drogue and the take-on aircraft/probe, a second distance between the tanker aircraft and the drogue, and a third distance between the tanker aircraft and the take-on aircraft. The drogue-probe coupling assist system is also designed to determine information relative to the necessary movement of the drogue and/or the necessary movement of the take-on aircraft to couple the drogue to the probe, as a function of the first, second, and third distance. | 01-06-2011 |
| 20110042520 | Aircraft Tank System, Refueling Unit And Method For Refueling An Aircraft - An aircraft tank system ( | 02-24-2011 |
| 20110108669 | VARIABLE SPEED DROGUE - The variable speed drogue includes a plurality of leading edge struts and trailing edge struts pivotally mounted to a refueling coupling member, and a drogue canopy connected between the trailing ends of the leading edge and trailing edge struts. A spring and an articulated strut brace assembly are connected between each of the leading edge and trailing edge struts. A center strut is pivotally connected to the trailing end of each leading edge strut, and each center strut includes a free end connected to a center portion of the canopy drogue. The drogue canopy is connected to the trailing ends of the leading edge and trailing edge struts such that the drogue canopy is movable between a radially inward position and a radially outward position, to provide substantially constant loads on the drogue within the range of refueling speeds. | 05-12-2011 |
| 20110147527 | TELESCOPING TUBE FOR TRANSFERRING FUEL - A telescoping tube for fuel transfer operations has a fixed part and a moving part, the moving part further having a dynamic sealing system which guarantees the sealing of the moving part against the fixed part, a cushioning system which absorbs the energy of the impact of the moving part against the fixed part in operations for extending and retracting the tube and protection systems against electrical discharges which ground the moving part to the fixed part, the aforementioned dynamic sealing, cushioning and protection systems all being incorporated in a single unit in the moving part of the telescoping tube. Additionally, the invention relates to an in-flight refuelling system for a tanker aeroplane, to carry out in-flight fuel transfer operations to a receiving aircraft, having a telescoping tube with the abovementioned characteristics. | 06-23-2011 |
| 20110147528 | METHOD AND SYSTEM FOR ENHANCED VISION IN AERIAL REFUELING OPERATIONS - System for providing an enhanced vision of an scenario from an observation place (10), particularly the refueling area of a receiving aircraft from a tanker aircraft during a refueling operation, comprising two high resolution cameras (4) for providing video signals of said scenario (92) for stereo monitoring and a three-dimensional monitoring system (31) for displaying three-dimensional images (17), image processing means (13) for performing a digital zoom of a selected zone (23) in the captured digital images (17) of the scenario (92) and means for displaying the zoomed images (25′, 25″) on said three-dimensional monitoring system (31) over or instead of the original digital images (17). The invention also refers to a method for providing an enhanced vision during a refueling operation including the viewing of three-dimensional zoomed images (25′, 25″) of a selected zone (23) of the refueling area (9). | 06-23-2011 |
| 20110147529 | METHOD AND SYSTEM FOR ENHANCED VISION IN AERIAL REFUELLING OPERATIONS - The invention relates to a system for providing enhanced vision of the refuelling scenario in aerial refuelling operations between a tanker aircraft ( | 06-23-2011 |
| 20110168844 | System for disconnecting a fuel transfer boom | 07-14-2011 |
| 20110180666 | SYSTEM AND METHOD FOR DISPLAYING AERIAL REFUELING SYMBOLOGY - In accordance with one or more embodiments, systems and methods for in-flight fuel delivery include an aerial refueling device adapted to provide fuel to a receiver aircraft, an optical component adapted to capture images of the aerial refueling device and the receiver aircraft, an operator input component adapted to interface with an operator and capture control signals as input from the operator, and a display component adapted to display images. A controller is adapted to receive the captured images and the captured control signals, process the control signals by generating graphic display symbology, process the images by generating a combined image having the generated graphic display symbology superimposed on the images, and display the combined image on the display component for viewing by the operator. The controller is adapted to superimpose the graphic display symbology on a portion of the images obscured by the aerial refueling device. | 07-28-2011 |
| 20110226905 | STABILIZED CONTROLLABLE DROGUE FOR AERIAL FLIGHT REFUELING - The stabilized controllable drogue for an inflight aerial refueling system includes a reception coupling, a paradrogue frame, a drogue canopy, and a plurality of actuators for moving the drogue canopy in a desired direction to control, steer and stabilize the stabilized controllable drogue during turbulent conditions. | 09-22-2011 |
| 20110272526 | SYSTEMS AND METHODS TO PROVIDE COMPLIANCE WITH STRUCTURAL LOAD REQUIREMENTS FOR AIRCRAFT WITH ADDITIONAL FUEL TANKAGE - Methods and systems are provided to comply with structural load requirements applicable to aircraft additional fuel tank systems. A plurality of aircraft fuel tanks may be positioned adjacent to one another, preferably within the fuselage (e.g., a cargo compartment) of the aircraft so as to be disposed generally along a longitudinal axis of the aircraft. The tank body defining an interior space for holding aircraft fuel, an intercommunication conduit assembly between the fuel tank modules configured to refuel and transfer fuel from the tank modules by a cascade mode and an intentional air-filled ullage space are operatively associated with the tank body to prevent an overpressure condition within the interior space of the fuel tank body. The intentional air-filled ullage is obtained through the predetermined positioning of the terminal open end of the intercommunication tube inside the respective fuel tank module. The intentional air-filled ullage can be configured in all or in only some of the fuel tank modules according to the design of the auxiliary fuel tanks or aircraft structural loads requirements. | 11-10-2011 |
| 20120025025 | Aircraft refuel system piping - The invention provides a pipe | 02-02-2012 |
| 20120037757 | BRAKING APPARATUS AND METHOD FOR AN AERIAL REFUELING BOOM SYSTEM - A braking apparatus of an aerial refueling boom system is provided to reduce the likelihood of or to prevent anomalous boom extension. The braking apparatus includes a pulley about which a cable wraps. The pulley is configured to be operably mounted to a first tube of the boom system and to rotate in response to movement of a second tube relative to the first tube as a result of the connection of the cable to the second tube. The braking apparatus also includes a lock, such as a brake or a pin lock, having open and actuated positions. In the actuated position, rotation of the pulley and movement of the second tube relative to the first tube are prevented. The lock is configured to be actuated by a reduction in performance of an actuation source that otherwise controls the relative positions of the first and second tubes. | 02-16-2012 |
| 20120043423 | AERIAL REFUELING BOOM AND BOOM PIVOT - An aerial refueling boom may include a refueling boom assembly and a pivot assembly for attaching the aerial refueling boom to a tanker aircraft. The refueling boom assembly may include a main boom section and a hollow telescoping boom section. The hollow telescoping boom section is adapted to be moved between a retracted position within the main boom section and an extended position extending from the main boom section for in-flight refueling of an aircraft. The pivot assembly may include an aircraft attachment plate to attach the pivot assembly to the tanker aircraft and a refueling boom attachment plate to attach the refueling boom assembly to the pivot assembly. The pivot assembly may also include a plurality of actuators pivotably coupling the aircraft attachment plate to the refueling boom attachment plate. | 02-23-2012 |
| 20120043424 | DROGUE DEPLOYING/RETRIEVAL METHOD - An in-flight refueling method may include deploying a fueling hose from a refueling aircraft. The fueling hose may have a drogue. The deployment of the fueling hose may include extending the drogue using a telescoping arm having a ring. The deployment of the fueling hose may also include passing the fueling hose through the ring to deploy the fueling hose. The in-flight refueling method may further include retrieving the fueling hose by drawing the drogue into a wire pitch mounted on the ring and collapsing the drogue in response to drawing the drogue into the wire pitch. | 02-23-2012 |
| 20120043425 | Refueling Equipment, and Method for Refueling An Aircraft Using Said Equipment - The invention relates to equipment for refueling an aircraft, including a pipe ( | 02-23-2012 |
| 20120104171 | ADAPTABLE BOOM REFUELING SYSTEM - Boom refuelling system ( | 05-03-2012 |
| 20120153084 | AUTOMATED RECEIVER AIRCRAFT IDENTIFICATION (ARAI) - An aerial identification and fuel inventory control system is disclosed. An RFID transponder mounted on a refueling aircraft transmits an identifier identifying the refueling aircraft in proximity to a fuel delivery aircraft. Substantially just prior to a start of fueling the refueling aircraft, the identifier is automatically logged in the fuel inventory control system. Upon completion of the fueling, a quantity of off-loaded fuel associated with the identifier is automatically logged in the fuel inventory control system. A fueling report may be automatically generated. | 06-21-2012 |
| 20120168564 | METHOD AND SYSTEM FOR A REFUELING DROGUE ASSEMBLY - A method and system for a refueling drogue coupling system are provided. The system includes a coupling latch assembly coupled to the coupling outlet wherein the coupling latch assembly includes a latch member configured to matingly engage a complementary latch-receiving member of a refueling probe. The coupling latch assembly further includes a latch member actuator operatively coupled to the latch member to permit the latch member to move from a first locked position to a second unlocked position. A probe position sensor is configured to detect a position of the refueling probe. A hose tension sensor is configured to measure a tension in a hose coupled to the coupling inlet. A drogue control system is positioned on the refueling drogue coupling system and communicatively coupled to the latch member actuator, the probe position sensor, and the hose tension sensor. | 07-05-2012 |
| 20120193478 | WING-MOUNTED REFUELING POD IN A TANKER AIRCRAFT - A refueling pod ( | 08-02-2012 |
| 20120199696 | AIR-TO-AIR REFUELING DROGUE ASSEMBLIES - An air to air refuelling drogue assembly includes a reception coupling and a drogue canopy connected to the reception coupling by connection means which hold the canopy in an operative, drag producing, position relative to the reception coupling during refuelling. The drogue assembly is arranged to controllably fail so as to reduce the drag load produced by the drogue when a drag load on the canopy exceeds a predetermined threshold. | 08-09-2012 |
| 20120267481 | PROTECTION OF LIQUID FUELS - The formation in a liquid hydrocarbon fuel of ice particles having a weight average particle size greater than 1 μm when said liquid hydrocarbon fuel is cooled to temperatures in the range of from 0 to −50° C. can be reduced or eliminated by use of at least one surfactant that is capable of dispersing water in said liquid hydrocarbon fuel to provide a stable clear water-in-oil microemulsion wherein the droplet size of the dispersed water phase is no greater than 0.25 μm. | 10-25-2012 |
| 20120273619 | AIRCRAFT AERIAL REFUELLING SYSTEM - An aircraft aerial refueling system including at least one pressure controlled fuel pump having a control system adapted to regulate the pump outlet fuel pressure using an outlet fuel pressure signal as control feedback. Also, methods of operating an aircraft aerial refueling system. | 11-01-2012 |
| 20120298805 | Aerial Refueling Drogue Deployment System - Systems and methods provide for a drogue deployment system that may be removably attached to a non-tanker aircraft to modify the aircraft for providing aerial refueling operations. Aspects of the disclosure provide a drum unit that may be secured in a cargo area of the non-tanker aircraft and connected to the fuel system of the aircraft. A drogue deployment unit may be removably attached to an external surface of the aircraft fuselage and includes a drogue extension tube that may be selectively deployed outward from the fuselage to provide separation between a refueling drogue and the aircraft. The drogue and corresponding refueling hose may be deployed from a drogue container attached to the drogue extension tube and extended rearward for providing fuel to a receiving aircraft. | 11-29-2012 |
| 20120305710 | SYSTEM FOR DETECTING THE STATUS OF A TUBE FOR FUEL TRANSFER - A system for detecting the status of a tube for fuel transfer. It includes a nozzle for a telescoping tube employed in air to air refueling and transfer of fuel on a tanker aircraft with a system that detects the status of the connection of the s nozzle with respect of a receptacle in a receiving aircraft, the system detecting the characteristics of the status of the connection of the nozzle in the receptacle by direct measurement of parameters in the nozzle itself of the tanker aircraft. | 12-06-2012 |
| 20130009011 | AIR TO AIR REFUELING SYSTEM WITH AN AUTONOMOUS ELECTRICAL SYSTEM - A system for air to air refueling with an autonomous electrical system, comprising at least two hose and drogue devices ( | 01-10-2013 |
| 20130020441 | Aerial Refueling System, Apparatus and Methods - An aerial refueling system utilizes the full drogue-probe coupling event as a control parameter for hose control. A variety of different types of signal sending and signal receiving devices may be used to indicate a coupling event between the drogue and probe. A positive coupling signal may serve to trigger a hose reel actuator to take up slack in the hose | 01-24-2013 |
| 20130068889 | WIRELESS REFUELING BOOM - A refueling boom is described. The refueling boom includes a non-telescoping portion configured to be coupled to a fuel tanker vehicle and a telescoping portion that is extendable and retractable relative to the non-telescoping portion. The telescoping portion includes a fuel nozzle. The refueling boom also includes a wireless communication system operable to enable wireless communication between a first location of the telescoping portion to a second location of the non-telescoping portion. The refueling boom also includes a control unit coupled to the telescoping portion. The control unit is operable to send first information to the fuel tanker vehicle via the wireless communication system and to receive second information from the fuel tanker vehicle via the wireless communication system. | 03-21-2013 |
| 20130075532 | FUELLING ARRANGEMENT AND METHOD - 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 destination is calculated by fuel calculation software on the basis of operational flight plan data, said actual zero fuel weight, and further data relevant to fuel consumption for that instance of the flight to the predetermined destination, said further data being processed interactively by the user by means of a user interface to said fuel calculation software, and subsequently fuel to meet said fuel requirement is uplifted to the aircraft under the control of said user. | 03-28-2013 |
| 20130119202 | REFUEL CONTROL SYSTEM AND METHOD OF REFUELLING - The invention provides a refuel control system for controlling refuel of at least one tank ( | 05-16-2013 |
| 20130126676 | REFUELLING EQUIPMENT AND METHOD FOR REFUELLING AN AIRCRAFT TANK SYSTEM - The aircraft refuelling equipment ( | 05-23-2013 |
| 20130161449 | LATCHING DETECTION AND INDICATION SYSTEM FOR AERIAL REFUELING COUPLINGS - Reception coupling unit of a hose and drogue device of a tanker aircraft with the probe of a receiver aircraft for in-flight refueling, including, respectively, first and second cooperating latching devices that can be positioned in one or more latching states in a refueling operation, in which the reception coupling unit includes at least a detector of the latching states and at least a first indication device and/or a second indication device for providing, respectively, to the pilot of the receiver aircraft and/or to the crew of the tanker aircraft indications that the cooperating latching devices are positioned in one or more of the latching states, the detector being operatively connected, respectively, to a first indication device and/or to a second indication device. | 06-27-2013 |
| 20130168497 | SYSTEMS AND METHODS FOR AIR VEHICLES - A refueling device for use in in-flight refueling operation between a tanker aircraft and a receiver aircraft includes a selectively steerable body and a controller. The selectively steerable body configured for being towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and includes a boom member having a boom axis and configured to enable fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during the in-flight refueling operation. The controller is configured for selectively steering the body to an engagement enabling position spaced with respect to the receiver aircraft and for aligning the boom axis in an engagement enabling orientation at the spaced position, and for subsequently moving the boom member along the boom axis towards the receiver aircraft for enabling fuel communication therebetween. | 07-04-2013 |
| 20130168498 | SYSTEMS AND METHODS FOR AIR VEHICLES - A method for controlling in-flight refueling of a receiver aircraft having a fuel receptacle, comprising: automatically steering a refueling device to an engagement enabling position, including: repeatedly determining a spatial disposition of the refueling device with respect to the receiver aircraft, the refueling device being capable of engaging and refueling the receiver aircraft via a boom member, when the device arrives to the engagement enabling position at which the boom member is in a predetermined spaced and spatial relationship with respect to the fuel receptacle of the receiver aircraft; repeatedly calculating steering commands based at least on the repeatedly determined spatial dispositions and characteristics of a spatial control system of the refueling device; sending the steering commands to the spatial control system; whereby at the engagement enabling position, the boom member of the refueling device is capable of engaging with the fuel receptacle to enable refueling of the receiver aircraft. | 07-04-2013 |
| 20130168499 | RAPID STORE LOAD SYSTEM FOR AIRCRAFT AND METHOD OF OPERATION THEREOF - A method to load stores on an aircraft, the method may be controlled by one or more controller and may include one or more acts of loading stores onto corresponding lift portions; determining a relative position of the aircraft; positioning the stores relative to the determined position of the aircraft; and securing the stores to corresponding hardpoints (HPs) of the aircraft. | 07-04-2013 |
| 20130264426 | Guidance apparatus of a tanker aircraft - A guidance apparatus mounted on the belly of a tanker aircraft for providing visual indications to the pilot of the receptor aircraft with respect to the approaching operation to carry out the refueling by means of a refueling boom. The guidance apparatus includes light emitting devices including modules of light emitting diodes and control devices for supplying current to the light emitting diodes that include dimming control units for controlling the intensity of the light emitted by the light emitting devices via a dimming signal depending on a dimming voltage. The dimming control units are adapted to provide to the light emitting devices a pulse-exponential amplitude modulated dimming signal so that the light intensity can be properly controlled in all visibility conditions. | 10-10-2013 |
| 20130299639 | Communication System - A communications system between a receiving aircraft and a tanker aircraft. The system includes a retractable tube with a nozzle which connects to a receiving aircraft receptacle, wherein the system comprises a primary device for sending/receiving data on the nozzle and a secondary device for sending/receiving data on the receptacle. The tanker and receiving aircraft transmit data by means of the devices only when the devices are both active and positioned opposite each other. In this way an indication is enabled to at least one of the two aircraft that the nozzle is correctly connected in the receptacle. | 11-14-2013 |
| 20130334370 | SYSTEM AND METHOD FOR THE CALCULATION OF THE APPROACH SPEED DURING AIR TO AIR REFUELLING OPERATIONS - Systems and methods for the calculation of the approach speed during air to air refuelling manoeuvres. The systems comprise: a) capturing means of a sequence of digital photograms of the approach operation scenario calibrated in order to determine the real distance corresponding to a pixel of a photogram; b) computational means configured for obtaining the coordinates of the relative trajectory of the receiver aircraft with respect of the tanker aircraft, by means of a sequence of photograms of the approach operation obtained by said capturing means and calculating the speed difference between receiver aircraft and tanker aircraft based on the trajectory defined by the coordinates recorded in said process b1). The invention also refers to the methods for calculating the approach speed. | 12-19-2013 |
| 20140021300 | Refueling Boom Disconnection System - A method and apparatus comprising a refueling controller. The refueling controller is configured to receive data about a current rate of movement of a refueling boom while the refueling boom is in contact with a receiver aircraft during flight. The refueling controller is further configured to disconnect the refueling boom from the receiver aircraft based on the current rate of movement of the refueling boom and a current position of the refueling boom. | 01-23-2014 |
| 20140042274 | Refueling Boom Control System - A method and apparatus comprising a refueling controller. The refueling controller is configured to receive a number of operator commands for moving a refueling boom on a tanker aircraft in a desired direction. The number of operator commands defines at least one of an azimuth movement and an elevation movement of the refueling boom during flight of the tanker aircraft. The refueling controller is further configured to generate a number of intermediate commands for moving the refueling boom in the desired direction as defined by the number of operator commands. The number of intermediate commands defines at least one of a roll movement and a pitch movement such that the refueling boom moves in the desired direction. | 02-13-2014 |
| 20140145033 | TENSIONING DEVICE FOR AIRCRAFT REFUELING BOOM HOIST - A power spring passively applies tension to a cable connected to an aircraft refueling boom. The power spring has a first end engaging a fixed arbor and second end engaging a rotatable spooling drum around which a portion of the cable is wound. The power spring biases the drum to rotate in a winding direction to apply tension to the cable, and the power spring stores energy when the drum rotates in an unwinding direction. The power spring may be located inside the drum or outside the drum. The drum may be actively driven by a motor that may be uncoupled from the drum to permit freewheeling rotation of the drum, wherein the power spring continues to apply tension to the cable. The invention eliminates reliance on one or more powered motors for removing unwanted slack in the cable. | 05-29-2014 |
| 20140158829 | IN-FLIGHT REFUELING SYSTEMS WITH A DIGITAL COMMUNICATION SUB-SYSTEM - The invention provides in-flight refueling systems with a communication sub-system available in radio silence operations including at least a first digital wireless data link comprising a first RF transceiver and a second RF transceiver coupled, respectively, to first and second antennas located in two points inside the boom or the hose of the refueling system or in RF communication with them and connected, respectively, to refueling control units in the tanker aircraft and in the free end of the refueling device by data buses allowing a digital communication between them. | 06-12-2014 |
| 20140203147 | TIP WITH NOZZLE LOAD SENSING AND WIRELESS COMMUNICATION FUNCTIONALITY FOR REFUELING BOOM - A Wireless Communication and Sensor System (WSCC) serving a refueled entity and a refueling entity, the system comprising nozzle load sensing functionality for a nozzle Boom Tip Unit; and apparatus for wirelessly transmitting loads sensed by the nozzle load sensing functionality to at least one of a boom operator and a boom flight control computer. | 07-24-2014 |
| 20140306063 | AERIAL REFUELING SYSTEM AND METHOD - A refueling system may include a refueling hose and a refueling drone coupled to the hose aft end. The refueling drone may be rearwardly deployable from the tanker aircraft such that the refueling drone is towed by the refueling hose behind the tanker aircraft. The refueling drone may be engaged to a receiver aircraft for transferring fuel from the tanker aircraft to the receiver aircraft. | 10-16-2014 |
| 20140319279 | AIRCRAFT REFUELING SYSTEM AND METHOD OF REFUELING AN AIRCRAFT - An aircraft refueling system for use with a supplying aircraft is provided. The refueling system includes at least two strips of material coupled to a lower portion of the supplying aircraft. The at least two strips are separated by a distance and comprise a material that facilitates the at least two strips becoming progressively visible to a pilot of a receiving aircraft as the receiving aircraft approaches the supplying aircraft. | 10-30-2014 |
| 20140346279 | SYSTEM AND METHOD FOR TRANSFERRING FUEL IN FLIGHT FROM A TANKER AIRCRAFT TO MULTIPLE RECEIVER AIRCRAFT - A trailing boom system for aerial refueling and a method for aerial refueling of multiple receiver aircraft. The trailing boom system for aerial refueling includes a parent pod capable of being connected to a wing of an aircraft, and a detachable pod releasable from the parent pod, the detachable pod including an extendible boom for refueling aircraft in flight. | 11-27-2014 |
| 20140353429 | SYSTEMS AND METHODS FOR WIRELESS DATA TRANSFER DURING IN-FLIGHT REFUELING OF AN AIRCRAFT - A refueling drogue assembly includes a drogue body coupled to a tanker aircraft, and at least one data transmission device coupled to the drogue body. The at least one data transmission device is configured to receive a transmission signal from a partner transmission device coupled to an airborne target aircraft. The transmission signal includes data to be stored. The drogue assembly further includes a data storage device coupled to the tanker aircraft. The data storage device is communicatively coupled to the at least one data transmission device. The data storage device is configured to receive the transmission signal and store the data. | 12-04-2014 |
| 20140353430 | DEVICES, SYSTEMS AND METHODS FOR REFUELING AIR VEHICLES - A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose. | 12-04-2014 |
| 20150041591 | MULTIPURPOSE FLYING BOOM - Embodiments provide a flying boom that is capable of refueling both receptacle-equipped aircraft and probe-equipped aircraft. In one embodiment, a flying boom includes a refueling tube at an end of the flying boom that is adapted to extend from the end of the flying boom to refuel receptacle-equipped aircraft. The flying boom further includes a retractable hose and drogue assembly at the end of the flying boom that is adapted to extend from the end of the flying boom to refuel probe-equipped aircraft. | 02-12-2015 |
| 20150076286 | REFUELING AIRPLANE - A refueling airplane converted from a non-refueling airplane having an original tail section and an original tail-strike pitch attitude. The refueling airplane comprises the original tail section and a recess formed therein, both constituting a modified tail section. The recess is configured to at least partially accommodate therewithin a refueling boom. The refueling boom is configured to be mounted to the modified tail section, such that a tail-strike pitch attitude of the refueling airplane, when said refueling boom is mounted thereto, is equal to or greater than the original tail-strike pitch attitude of the non-refueling airplane. | 03-19-2015 |
| 20150083864 | SYSTEM AND METHOD FOR INDICATING PRESSURE IN AERIAL REFUELING ASSEMBLY - An aerial refueling assembly includes, for example, a pressure transducer, a processor, and one or more light sources. The processor is coupled to the pressure transducer. The one or more light sources are coupled to the processor. The pressure transducer is configured to sense a fuel pressure inside the aerial refueling assembly and to provide a signal that is indicative of the sensed fuel pressure inside the aerial refueling assembly. The processor is configured to receive the signal and to cause the one or more light sources to flash in a manner that relates to the sensed fuel pressure. | 03-26-2015 |
| 20150136911 | DEVICES, SYSTEMS AND METHODS FOR REFUELING AIR VEHICLES - A variety of refueling devices, systems and methods are disclosed for use in in-flight refueling. In one example one such device is towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and has a boom member with a boom axis. The boom member enables fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during in-flight refueling. The device maintains a desired non-zero angular disposition between the boom axis and a forward direction at least when the refueling device is towed by the tanker aircraft in the forward direction via the fuel hose. | 05-21-2015 |
| 20150344147 | AERIAL REFUELING COUPLING FOR IN-FLIGHT OPERATION PARAMETER MEASURING - The present disclosure refers an aerial refueling coupling for in-flight parameter measuring, including a body configured to receive and support a probe and a removable shell that covers at least part of the body. The aerial refueling coupling includes a sensor system for detecting at least one parameter related to in-flight refueling operation, a data processing device configured to provide a measure at least relative to parameters detected by the sensor system, a portable storage system, and a power supply system comprising at least on battery for supplying energy, and a ram air turbine for their activation when the aerial refueling coupling is in-flight. The data processing device, the storage system and the power supply system are mounted onto the body covered by the shell. | 12-03-2015 |
| 20150353202 | BRAKING APPARATUS AND METHOD FOR AN AERIAL REFULEING BOOM SYSTEM - A braking apparatus of an aerial refueling boom system is provided to reduce the likelihood of or to prevent anomalous boom extension. The braking apparatus includes a pulley about which a cable wraps. The pulley is configured to be operably mounted to a first tube of the boom system and to rotate in response to movement of a second tube relative to the first tube as a result of the connection of the cable to the second tube. The braking apparatus also includes a lock, such as a brake or a pin lock, having open and actuated positions. In the actuated position, rotation of the pulley and movement of the second tube relative to the first tube are prevented. The lock is configured to be actuated by a reduction in performance of an actuation source that otherwise controls the relative positions of the first and second tubes. | 12-10-2015 |
| 20160001891 | System and Method for Identifying a Receiving Aircraft During Airborne Fueling - A system for effecting automatic identifying of a receiving aircraft receiving fuel from a fuel delivery apparatus in a delivering aircraft during an airborne fueling operation includes: (a) a first unit coupled with the receiving aircraft; (b) a second unit coupled with the delivering aircraft; and (c) a processing unit coupled with at least one of the first unit and the second unit. The first and second units cooperate to effect communicative coupling for conveying identifying information between the receiving aircraft and the delivering aircraft. The processing unit cooperates with at least one of the first unit and the second unit for employing the identifying information to effect the identifying. | 01-07-2016 |
| 20160023775 | REFUELING BOOM CONTROL SYSTEM - An apparatus comprising a refueling controller. The refueling controller is configured to receive a number of operator commands for moving a refueling boom on a tanker aircraft in a desired direction. The number of operator commands defines at least one of an azimuth movement and an elevation movement of the refueling boom during flight of the tanker aircraft. The refueling controller is further configured to generate a number of intermediate commands for moving the refueling boom in the desired direction as defined by the number of operator commands. The number of intermediate commands defines at least one of a roll movement and a pitch movement such that the refueling boom moves in the desired direction. | 01-28-2016 |
| 20160039531 | SYSTEMS AND METHODS FOR AIR VEHICLES - A refueling device for use in in-flight refueling operation between a tanker aircraft and a receiver aircraft includes a selectively steerable body and a controller. The selectively steerable body configured for being towed by a tanker aircraft via a fuel hose at least during in-flight refueling, and includes a boom member having a boom axis and configured to enable fuel to be transferred from the fuel hose to a receiver aircraft along the boom axis during the in-flight refueling operation. The controller is configured for selectively steering the body to an engagement enabling position spaced with respect to the receiver aircraft and for aligning the boom axis in an engagement enabling orientation at the spaced position, and for subsequently moving the boom member along the boom axis towards the receiver aircraft for enabling fuel communication therebetween. | 02-11-2016 |
| 20160075441 | AERIAL REFUELING NAVIGABLE DEVICE, SYSTEM AND METHOD - A device, system, and method for facilitating aerial refueling. The device is a navigable flying unit for more precise positioning to establish a fuel-transmitting connection with a fuel inlet of a fuel-receiving plane (including a fuel inlet located on the wing of a commercial aircraft). The device comprises controllable aerodynamic surfaces for mid-air maneuvering while attached to a fuel-transmitting medium being trailed by a fuel-giving plane. The navigable unit may also comprise a means for, if necessary, moving along a surface of the fuel-receiving plane for more precise positioning, and a means for attaching to the surface of the fuel-receiving plane and/or a fuel port thereof, as well as a means for coupling with the fuel inlet in order to establish a fuel-transmitting connection. The in-air maneuvering of the device and fuel-transmitting medium may be facilitated in one embodiment, by the fuel-transmitting medium comprising aerodynamic surfaces configured for reducing drag. | 03-17-2016 |
| 20160083105 | RECEPTION COUPLING - A reception coupling for air-to-air refuelling has a main body and a fuel passage. A moveable valve member is provided for opening and closing the fuel passage. A chamber is separate from the fuel passage. A portion of the valve member can be accommodated in the chamber as the valve member moves toward an open position, shielding that portion from effects of pressure in the fuel passage. | 03-24-2016 |
| 20160090188 | QUICK RELEASE SYSTEM FOR A COUPLING AND DROGUE ASSEMBLY - The invention refers to a quick released system for coupling ( | 03-31-2016 |
| 20160376020 | Aircraft Receptacle - A system and method for an aircraft receptacle. The aircraft receptacle comprises an actuator connected to a number of latches and a tension spring connected to the number of latches. The actuator is part of an actuation system. The elastic member holds the number of latches in a disengaged position after failure of the actuation system. | 12-29-2016 |
| 20170233092 | TELESCOPING STOWAGE TUBE AND ROTATING HOSE REEL FOR CARGO BAY REFUELING SYSTEM | 08-17-2017 |
| 20100163680 | System and Method For a Fuel Bladder Assembly With Internal Netting - Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto; and a netting disposed within the fuel bladder and disposed to prevent collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV). | 07-01-2010 |
| 20100163681 | System And Method For A Fuel Bladder Assembly With Spiral Tubing - Systems and methods provide for a flexible fuel bladder assembly disposed to store fuel and supply the fuel to a vehicle. The flexible fuel bladder assembly may include: a fuel bladder including a fuel-resistant film disposed to store the fuel and supply the fuel therefrom at a manifold assembly connected thereto; and a spiral tubing disposed within the fuel bladder and disposed to prevent collapsing of any two or more sides of the fuel bladder upon each other and permit a substantial portion of the fuel to be supplied from the fuel bladder to the manifold assembly in an uninterrupted fashion until the substantial portion of fuel is removed from the fuel bladder. The flexible fuel bladder may be used in an unmanned aerial vehicle (UAV), which may be any one of: an organic air vehicle (OAV), a micro air vehicle (MAV), an unmanned ground vehicle (UGV) or an unmanned combat air vehicle (UCAV). | 07-01-2010 |
| 20100200700 | TANKS FOR CONTANING A FLUID WITHIN A CHAMBER - A tank for containing a fluid, such as fuel, oil or gas within a chamber. The walls of the chamber are partially defined by a rigid structure having an opening; and partially defined by an elastomeric diaphragm which is attached around its periphery to the rigid structure and covers the opening in the rigid structure. An attachment frame engages the diaphragm and the rigid structure, and extends around the periphery of the diaphragm. The attachment frame has a first portion which engages the diaphragm, and a second portion which is positioned outside an outer edge of the diaphragm and attached to the rigid structure. | 08-12-2010 |
| 20110266394 | FUEL GAUGE FOR AN UNMANNED AERIAL VEHICLE - An amount of fuel in a fuel bladder of an unmanned aerial vehicle (UAV) is determined based on a deformation of the bladder. In some examples, a fuel system for a UAV includes a bladder, a proximity sensor, a fuel gauge, and a controller. The bladder is deformable based on the amount of fuel in the bladder. The proximity sensor may output a signal that varies as a function of the deformation of the bladder. The controller may determine the amount of fuel in the bladder based on the signal output by the proximity sensor and control the fuel gauge to indicate the determined amount of fuel. | 11-03-2011 |
| 20120305711 | INTEGRAL THERMALLY INSULATED FUEL BLADDER - A method and apparatus for thermally decoupling fuel from an airframe structure is provided. In some aspects, an apparatus may include a bladder wall having stratified refractory fabric and refractory metal, and a sealant coating an internal surface of the bladder wall. The bladder wall may be configured to maintain an internal surface temperature of 300° F. or less when exposed to an external surface temperature of at least 500° F. | 12-06-2012 |
| 20130214095 | SLEEVE AND ROD SUPPORT FOR FUEL BLADDER - A flexible fuel bladder structure for an aircraft includes one or more sleeves extending along an exterior of the fuel bladder. The one or more sleeves are receptive of one or more rods to at least partially suspend the fuel bladder in the aircraft. An aircraft includes a fuselage and a flexible fuel bladder disposed in the fuselage. One or more rods are installed through a portion of the fuel bladder and into a fuselage member. The flexible fuel bladder is at least partially suspended from the one or more rods. A method of installing a fuel bladder in an aircraft includes inserting a flexible bladder into a fuselage space of the aircraft. One or more rods are installed through one or more fuselage members and one or more sleeves of the fuel bladder. The one or more rods at least partially suspend the fuel bladder in the fuselage. | 08-22-2013 |
| 20150336680 | Tank System For The Cryogenic Storage Of Hydrogen, And Aircraft With A Tank System For The Cryogenic Storage Of Hydrogen - A tank system for the cryogenic storage of hydrogen includes a tank structure with at least one hollow body for accommodating liquid hydrogen and at least one insulating means, which encloses the tank structure, for insulating the at least one hollow body. The tank structure has an exterior shape that is integrateable in a load-bearing primary structure of an aircraft. The tank structure is load bearing and is designed to at least partially absorb a load introduced into the primary structure. This makes it possible to achieve a particularly efficient design of an aircraft in which the fuselage of the aircraft is not divided into two parts by the hydrogen tank integrated therein, can be arranged near the center of gravity, and essentially does not increase the additional weight of the aircraft. | 11-26-2015 |
| 20160075440 | EXTERNAL-BLADDER FUEL SYSTEM - Provided is a bladder external to a fuel tank of a vehicle and allows an operational range of the vehicle to be increased. Preferably the bladder is external to rest of the vehicle and the vehicle is an aircraft. The external bladder allows fuel in the fuel tank to expand and contract without requiring additional space within the vehicle, thus allowing more fuel mass to be held by the vehicle and a smaller vehicle profile that is more aerodynamically efficient. More preferably, the bladder is disconnectable from the rest of the vehicle to allow increasing of aerodynamic efficiency and weight reduction during use. | 03-17-2016 |
| 20160096630 | AIRCRAFT HYBRID FUEL SYSTEM - An aircraft hybrid fuel system includes a main tank and a set of flexible bladders, the main tank and the set of flexible bladders defining a fuel containment space. The system further includes a set of pathways coupling the set of flexible bladders to the main tank. The set of pathways is constructed and arranged to vent gas out of the set of flexible bladders into the main tank while fuel from a fuel source is provided into the fuel containment space defined by the main tank and the set of flexible bladders. Along these lines, each flexible bladder can be provisioned with a fuel port to provide fuel, and a separate vent port to vent gas to the main tank. | 04-07-2016 |
| 20090272851 | METHOD AND DEVICE FOR CORRECTING THE LATERAL DISSYMMETRY OF AN AIRCRAFT - Method and device for correcting the lateral dissymmetry of an aircraft. | 11-05-2009 |
| 20100012786 | GIMBALED, ARTICULATED AND SLIDING SINGLE AND DUAL WALL PRESSURE BALANCED TRANSFER TUBES - The present invention provides an apparatus and method for connecting two sub-flow systems (e.g. airplane fuel tanks) and conveying a fluid between the two sub-systems using a pressured balanced transfer tube, particularly when there are large radial and axial movements or offsets between the sub-systems. Unlike conventional fluid transfer systems, the present apparatus and method allow for the pressure in the transfer tube to be balanced to internalize the pressure forces and prevent the exertion of pressure forces on the sub-systems connected to the transfer tube. | 01-21-2010 |
| 20100044515 | CONTINUAL TRANSFERENCE OF FUEL BETWEEN FUEL TANKS AT A RATE COMMENSURATE WITH FUEL BURN DURING CRUISE FLIGHT OPERATION TO MAINTAIN THE AIRCRAFT CENTER OF GRAVITY WITHIN A PRE-SELECTED AFT CENTER OF GRAVITY ENVELOPE - Fuel transference between aircraft fuel tanks, disposed in different locations, is used to maintain the aircraft Center of Gravity close to the aft limit of the certified Center of Gravity versus weight envelope. Continuous fuel transfer decreases the control band thus enhancing aircraft performance. | 02-25-2010 |
| 20100059630 | BUNDLE COMPRISING TWO PAIRS OF TANKS, AND AN AIRBORNE LAUNCHER INCLUDING SUCH A BUNDLE - The bundle comprises two pairs of same-volume cylindrical tanks, each pair comprising two tanks containing a same-density propellant suitable for flowing at the same volume flow rate, the four tanks being fastened directly to one another via reinforcing hoops in such a manner that the center of gravity of each of said pairs remains continuously on the axis of said bundle while the propellants are flowing. | 03-11-2010 |
| 20110147530 | AUXILIARY FUEL TANK SYSTEM - 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 operatively connected to the ejector system, and/or at least one aft tank operatively connected to the ejector system. The forward and/or at least one aft tank transfer fuel to the main tank using gravity. | 06-23-2011 |
| 20110226906 | METHOD OF CONTROLLING THE CENTRE OF GRAVITY OF AN AIRCRAFT - A method of controlling the centre of gravity of an aircraft having a plurality of fuel tanks, the method comprising transferring fuel from one or more of the fuel tanks according to a predetermined sequence, the timing of the sequence being dependent on the decrease in gross weight of the aircraft. | 09-22-2011 |
| 20130320146 | TANK, A FUEL STORAGE SYSTEM, AND AN AIRCRAFT - A storage tank ( | 12-05-2013 |
| 20140027575 | FUEL TRANSFER SYSTEM CONTROLLED BY FLOAT VALVES - A fuel transfer system for an aircraft includes an upper tank, a lower tank, a fuel transfer line connecting the upper tank to the lower tank, an upper fuel transfer line outlet in the lower tank, a lower fuel transfer line outlet in the lower tank, an upper float valve associated with the upper fuel transfer line outlet, and a lower float valve associated with the lower fuel transfer line outlet. The upper fuel transfer line outlet, which is in the lower tank, is in fluid communication with the upper tank. The lower fuel transfer line outlet, which is located in the lower tank, is in fluid communication with the upper tank. | 01-30-2014 |
| 20150321767 | SYSTEM FOR TEMPERATURE AND ACTUATION CONTROL AND METHOD OF CONTROLLING FLUID TEMPERATURES IN AN AIRCRAFT - A system for fluid temperature control and actuation control for an aircraft engine fueled by dual fuels. The system includes a first fuel system having a first fuel tank fluidly coupled to the engine, a second fuel system having a second fuel tank fluidly coupled to the engine, with the second fuel being different from the first fuel and having a different temperature than the first fuel, a fuel distribution unit (FDU) fluidly coupled to the first fuel tank of the first fuel system, and a fuel-to-fuel cooler (FFC) configured to transfer heat between the first fuel in the first fuel system and the second fuel in the second fuel system. | 11-12-2015 |
| 20150344143 | AIRCRAFT AND METHOD OF MANAGING EVAPORATED CRYOGENIC FUEL - A method of managing evaporated cryogenic fuel in a storage tank of a cryogenic fuel system of an aircraft and an aircraft having at least one turbine engine providing propulsive force for the aircraft and a cryogenic fuel system including a passively cooled cryogenic fuel storage tank located within the aircraft, a pressure vent fluidly coupled to the cryogenic fuel storage tank and exhausting evaporated gas from the cryogenic fuel to define a natural gas vent stream, and a catalytic converter fluidly coupled to the pressure vent. | 12-03-2015 |
| 20150344144 | CRYOGENIC FUEL SYSTEM AND METHOD FOR DELIERING FUEL IN AN AIRCRAFT - A cryogenic fuel system for an aircraft having a turbine engine with a compressor section and a combustion chamber, including a tank for storing cryogenic fuel, a supply line operably coupling the tank to the combustion chamber and a pump coupling the tank to the supply line to pump the cryogenic fuel at high pressure through the supply line where the pump is operably coupled to the compressor such that operation of the turbine engine drives the pump and a method for delivering fuel in a fuel system to a turbine engine. | 12-03-2015 |
| 20150344145 | AIRCRAFT AND A RETROFIT CRYOGENIC FUEL SYSTEM - An aircraft having a turbine engine having a bleed air output line, a cryogenic fuel system having a cryogenic fuel tank for storing cryogenic fuel and a supply line operably coupling the tank to the turbine engine, and an on board inert gas generating system (OBIGGS) fluidly coupled to the bleed air output and having a nitrogen rich stream output line and an oxygen rich stream output line. | 12-03-2015 |
| 20160375985 | CONTINUOUS FUEL TANK LEVEL CONTROL - A method of aircraft fuel distribution includes selecting a longitudinal center of gravity and predicting a rate of change of the center of gravity during flight. Fuel is located in a tail fin tank of a vertical tail fin of the aircraft, and is transferred from the tail fin tank forward at a predetermined transfer rate to counteract the predicted rate of change thereby maintaining the selected center of gravity. An aircraft fuel distribution system includes a center main fuel tank, a tail fin tank and a tail fin fuel pump to pump fuel between the tail fin tank and the center main fuel tank. An electronic controller operates the tail fin fuel pump such that fuel is flowed between the tail fin tank and the center main fuel tank at a predetermined transfer rate to maintain automatically an optimal position of a longitudinal center of gravity of the aircraft. | 12-29-2016 |
