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JP6067205B2 |
To provide a method for more conveniently and efficiently manufacturing a nitrogen-enriched air to be used for explosion-proof of an aircraft etc.The method is provided for manufacturing the nitrogen-enriched air by supplying air of a hi...
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JP6060165B2 |
A system includes a composite structure and a bushing. The composite structure includes an opening defined therethrough. The bushing includes a cylindrical body sized to be secured within the opening in an interference fit to facilitate ...
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JP6044140B2 |
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JP6029421B2 |
To provide a nitrogen enriched air (NEA) supply system which easily maintains low the concentration of oxygen within a tank before fueling. In the present invention, a subsidiary pipe 20b that directly supplies NEA to a spill-back pipe 2...
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JP6029422B2 |
The present invention intends to extend the operating life of an air separation module (ASM) in a nitrogen enriched air (NEA) supply system by controlling the temperature of bleed air as a supply source of the NEA. The NEA supply system ...
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JP6018065B2 |
A dual fuel propulsion system comprising a gas turbine engine configured to generate a propulsive thrust using a cryogenic liquid fuel.
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JP5990081B2 |
A system (10) for wirelessly refueling an aircraft (12) includes an aircraft (12) having a fuel tank (20), a control valve (26), a fuel sensor (22) outputting a fuel signal indicative of the amount of fuel in the at least one fuel tank (...
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JP5972383B2 |
A method and apparatus for electrostatically bonding coaxial tubing. An outer tube comprises an electrically conductive material and has an inner surface. An inner tube comprises material and has an outer surface. The inner tube and the ...
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JP5972967B2 |
The objective of the present invention is to provide: a fuel tank that can prevent an increase in weight and can have reduced cost and working time during a production process, a main wing; an aircraft fuselage; an aircraft, and a mobile...
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JP5963855B2 |
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JP5922112B2 |
There is provided a method for mitigating static discharge in a fuel container. The method provides a static dissipative coating having a volume resistivity of 1.0×109 Ω-m (ohm-meter) or less when measured at 40 V (volts) or less, havi...
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JP2016512862A |
How to use cryogenic temperature fuel (12) within an engine (101) for airplanes (5) which generate waste heat, A step which supplies cryogenic temperature fuel (12) of a fluid for combustion within an engine (101), and a step which evapo...
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JP2016510376A |
A cryogenic fuel system for aircraft with a turbine engine with a compressor section and a combustion chamber has a tank for storing cryogenic fuel, a supply line that operatively connects the tank to the combustion chamber, and a tank. ...
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JP2016510278A |
The method of managing the evaporated cryogenic fuel in the storage tank of the cryogenic fuel system of the aircraft is to release the gas in the form of the evaporated cryogenic fuel from the storage tank to maintain the internal press...
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JP2016509550A |
The aircraft has a turbine engine with a bleed air discharge line, a cryogenic fuel tank for storing cryogenic fuel and a cryogenic fuel system with a supply line operably connected to the turbine engine, and fluid in the bleed air disch...
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JP2016509549A |
The aviation power system is a turbine engine that is coupled to the aircraft to provide propulsion and radiate heat during operation to determine a high temperature source, and is located inside the aircraft to fuel the turbine and from...
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JP2016509645A |
Fluid temperature control and operation control systems for aircraft engines fueled with dual fuels are a first fuel system with a first fuel tank fluidized to the engine and a second fluid connected to the engine. In the second fuel sys...
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JP2016508912A |
A method of managing boil-off from an LNG tank on board an aircraft includes removing the boil-off from the aircraft and disposing of the removed boil-off from the aircraft. The step of discarding the removal boiloff can include the step...
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JP2016503150A |
The system in one embodiment includes a heat exchanger, a detection unit, and a controller. The heat exchanger includes a first passage and a second passage, and is configured to exchange heat between them. The first passage is configure...
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JP2016502622A |
The turbine engine assembly evaporates a turbine core with a compressor part, a combustion part, a turbine part, a nozzle part, a liquefied natural gas (LNG) reservoir, an evaporator heat exchanger, and an LNG reservoir. A first liquid s...
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JP2016500597A |
Methods and devices for covering the fastener system (102) are provided. In one exemplary embodiment, the device comprises a cover (100). The cover (100) is configured to rest on the fastener system (102) on the surface (101) of the obje...
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JP5820876B2 |
The valve actuator (1) includes a housing (2), a motor (4) coupled to the valve, wherein rotation of the motor (4) changes the position of the valve from a first position in which fluid flow may occur along at least one path and a second...
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JP5822493B2 |
A long-life lightning protection fastener or the like to prevent explosion for aircrafts at low cost is provided, the fastener having a light weight, ensuring sufficient lightning protection, and having extremely less failures and high r...
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JP2015186804A |
To provide a method for more conveniently and efficiently manufacturing nitrogen-enriched air to be used for explosion-proof of an aircraft or the like.A method manufactures nitrogen-enriched air by supplying air of high temperature of 1...
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JP5798045B2 |
A fuel system comprising a liquid fuel tank, an engine, and a cyclonic separator having an inlet fluidically connected to the fuel tank, a first outlet fluidically connected to an engine fuel feed system, and a second outlet. The cycloni...
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JP5791681B2 |
Hydrogen powered air vehicles that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 60,000 ft carrying payloads of up to 2,000 pounds. Embodiments may include features such as large wingspan relati...
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JP5775460B2 |
A method of operating an aircraft fuel management system for an aircraft having at least one fuel tank, each fuel tank having an associated fuel quantity indicator arranged to provide an indication of the amount of fuel in the associated...
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JP5737903B2 |
A tube support structure for an aircraft includes: a parallel movement mechanism configured to support the tube movably in parallel; and an angle adj ustment mechanism configured to support the tube angle-adjustably. The parallel movemen...
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JP2015515940A |
The aviation fuel tank system comprises at least one fuel tank (20), the at least one fuel tank (20) being configured to ventilate multiple interconnected chambers and air (32) into the interior. The system is configured to guide the air...
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JP2015514618A |
Modular components used within the system are provided to inactivate the vacant spaces in the aircraft. Modular components include bundles of hollow fiber and tube sheet membranes, low temperature ozone converters, hollow fiber shells, a...
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JP2015513941A |
At least one oxygen-poor air having at least one fuel cell system, at least one drying device connected to the fuel tank, a first outlet connected to the cargo hold and a second outlet connected to the drying device. A fuel cell / deacti...
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JP5695738B2 |
The aircraft refuelling equipment (20) of an aircraft comprises a pipework (22) in which a fuel supply line (13) is connected to a plurality of tank supply lines, fuel tanks connected to tank supply lines of the pipework, first valves (2...
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JP5658723B2 |
A method for improving conductance on hydraulic fittings (20) by incorporating a soft metal interlayer (16) between the fitting and a hydraulic tube (12,14), wherein the soft metal interlayer (16) is located in an area where the fitting ...
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JP2015009707A |
To provide an unmanned helicopter capable of suppressing a fuel pump from sucking in air regardless of a flight state.The unmanned helicopter includes a fuel tank 48 for holding fuel to be supplied to driving source. The fuel tank 48 inc...
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JP2015500761A |
An in-flight inert gas generator system for an aircraft receives air from a relatively low pressure source such as low pressure engine bleed or ram air and sends this air to a positive displacement compressor (40) to an air separation mo...
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JP2015500162A |
An in-flight inert gas generator system for an aircraft receives air from a relatively low pressure source such as low pressure engine bleed or ram air and sends this air to a positive displacement compressor (40) to an air separation mo...
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JP5628813B2 |
An aircraft panel which is a wall of a fluid tank when in use, the panel comprising a skin layer with an outer surface which is an aerodynamic surface of an aircraft when in use; a hole in the skin layer; an ultrasonic gauge which is mou...
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JP2014184802A |
To provide an implement capable of safely and easily draining a fuel remaining in a fuel tank by a simple configuration without damaging the airframe of an aircraft.A fuel draining implement 20 for draining a fuel from a fuel drain valve...
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JP5592257B2 |
The disclosed embodiments relate to a fuel line valve for an aircraft, that includes a shell capable of rotation inside the valve body and connected to a driving shaft driven by an electric actuator. The valve further includes a torque g...
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JP5579391B2 |
An article manufactured in a mould and which comprises a structural composite of plastics layers, the article having a wall defining an internal space for holding contents therein; wherein, the wall is formed from at least two layers of ...
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JP5479896B2 |
An aircraft including a fuselage including a cabin to accommodate persons and/or a load, and a propulsion system. The propulsion system includes at least one tank and/or one combustion chamber, wherein part of the propulsion system can b...
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JP5438016B2 |
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 i...
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JP5431927B2 |
Hydrogen powered air vehicles that in some embodiments can fly with very long endurance (10 or more days) at altitudes over 60,000 ft carrying payloads of up to 2,000 pounds. Embodiments may include features such as large wingspan relati...
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JP5427562B2 |
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JP2013545649A |
An aircraft system comprising a fuel storage system comprising a first fuel tank capable of storing a first fuel and a second fuel tank capable of storing a second fuel is disclosed herein. The aircraft system further comprises a fuel ce...
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JP2013256284A |
To provide a method and apparatus for limiting the flow of electric current, induced by an event such as lightning or an electrical fault, along a fluid transport system and allowing static dissipation along the fluid transport system.A ...
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JP5373639B2 |
A method of removing water (7) from a fuel tank (2) using a water scavenging line (4) which has an inlet (6) immersed in the water and an outlet (5) coupled to a water tank (3). The method comprises filling the fuel tank with fuel (30) w...
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JP2013542874A |
A cryogenic fuel storage system for an aircraft is disclosed including a cryogenic fuel tank having a first wall forming a storage volume capable of storing a cryogenic liquid fuel; an inflow system capable of flowing the cryogenic liqui...
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JP5331453B2 |
A fabrication method for providing a relatively smooth surface associated with lightning strike protection for composite materials (14) joined with fasteners (10) recessed below the surface (12) is described. The method includes coating ...
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JP5330534B2 |
A fuel monitoring system for automatically monitoring a fuel transfer in an aircraft fuel system, the fuel system including a plurality of fuel tanks, the fuel monitoring system comprises a fuel quantity sensor arranged to measure the qu...
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