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JP2013513518A |
Disclosed is an electric accumulator for selectively operating at least one aircraft device. The electric accumulator includes an ultra-capacitor array for storing electrical energy, which can later be used to power an aircraft device. T...
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JP2013505172A |
An electric power management system of a vehicle may interconnect a power plant, a propeller drive unit, and a battery via a bus. A command limiting controller may direct the operation of the power plant and the propeller drive unit in f...
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JP5134371B2 |
An engine (101) propels the aircraft. A fuel cell (102) supplies electric energy to the aircraft. A kerosene reservoir (103) supplies the engine with engine fuel. A hydrogen reservoir (104) supplies the fuel cell with fuel cell fuel. The...
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JP5112068B2 |
Systems and methods for operating aircraft power systems are disclosed. A power system in accordance with one embodiment of the invention includes an aircraft auxiliary power unit and a controller coupled to the aircraft auxiliary power ...
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JP5111598B2 |
In order to generate an efficient aerodynamic braking force, whatever the speed of a vehicle such as an airplane flying in the air, the method includes a step for the production of energy by the vehicle, a step of storage of the energy p...
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JP5083560B2 |
To adequately supply a proper amount of air with proper pressure independent from flight altitude to a fuel cell mounted on an aircraft by effectively using pressure energy of air inside the aircraft and heat energy discharged from the f...
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JP2012197073A |
To provide an aircraft capable of hovering, which can improve flying safety, can expand a fuel region so as to make a longer mission possible, and can largely improve speed and acceleration performance under a particularly sever, for exa...
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JP5037572B2 |
An inlet duct for an auxiliary power unit comprises an inlet end, and extends to an outlet end. At least one splitter (34,40) is positioned within the duct and between the inlet end and the outlet end to sub-divide an interior of the duc...
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JP5016706B2 |
A starter generator has an electric rotating machine having a rotating shaft. The rotating machine is designed to carry on two reverse operations- motor and generator. A first clutch is connected between the rotating machine and the firs...
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JP5020100B2 |
A device supplying electricity power to and actuating equipments of a gas turbine airplane engine, including an electricity power supply circuit dedicated to the engine and distinct from an electricity network on board the plane and exci...
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JP5009298B2 |
A device for controlling power transfer between two cores of a direct current network, in which the cores, which are source-charge interconnection nodes, include protective and contact members, placed in different areas of a power distri...
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JP4989463B2 |
The aircraft has a fluid duct system (26) for suction of a boundary layer and cleaning of fluid in endangered places of an outer skin of the aircraft. The duct system is connected to a pumping device that is driven, by cabin exhaust air,...
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JP4987876B2 |
A combined device for instantaneous control of power transfer between two cores of a direct current network and for powering an alternating current engine. The device includes: an assembly of two three-phase inverters, each including thr...
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JP4979679B2 |
The system has a fuel cell stack (41) comprising a set of fuel cells, and oxygen and hydrogen tanks (51, 61) attached to the cell stack for supplying oxygen gas and hydrogen gas to the cells. The tanks (51, 61) are oxygen and hydrogen co...
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JP4974694B2 |
A non-aircraft-propelling auxiliary gas turbine engine (10) installable in an aircraft (12) having a cabin (16) adapted to be pressurized. The auxiliary gas turbine engine includes an auxiliary-gas-turbine-engine compressor (18) having a...
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JP4897830B2 |
Emergency supply device (1) has back pressure turbine (2) propelled by air flow (14) and an energy transducer (4) which partially maintains the function of a hydraulic system or an electrical system on boarding an airplane in an emergenc...
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JP4881944B2 |
The supply system comprises an onboard vapor generator which generates hot water vapor with hydrogen and oxygen supplied from corresponding feed unit. A mixer (132) controls a quantity of water supplied to the vapor generator, from a wat...
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JP2012025349A |
To provide a flying object that can be miniaturized without the need for an external supply of electric power, and to provide a system and method for flying.The flying object 100 includes: a body 110; a propeller for propelling the body ...
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JP2012503569A |
A power distribution system for an aircraft having at least one engine includes at least one torque transmission means that is movably held and is connected to at least one shaft of the engine and extends from the shaft of the engine to ...
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JP2012001203A |
To provide a starter for an auxiliary power unit that alleviates the torque shock and reduces damage and breakage of a starter shaft when a clutch is engaged.The starter for the auxiliary power unit includes a direct current motor operab...
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JP2012002223A |
To provide a starter for an auxiliary power source, which damps torque shock at clutch engagement and reduces the damage and breakage of a starter shaft.A starter for an auxiliary power source includes a direct current motor operably con...
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JP4786647B2 |
The suction arrangement has suction surfaces in critical flow areas. A suction pipe (23) is connected between the suction surface and a compressor (24) of a turbo-supercharger (2). A branch pipe (10) is connected between a high-pressure ...
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JP4700113B2 |
This invention provides an aircraft electric generation system (1), which can achieve significantly increased capacity of electric generation, while adequately suppressing unwanted increase of a front face area of an aircraft engine as w...
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JP2011511731A |
An aircraft fuel cell system includes a fuel cell which has an oxidant inlet for supplying an oxygen-containing medium to the fuel cell. An oxidant supply line has a first end which is connected to the oxidant inlet of the fuel cell. A s...
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JP2011511207A |
Engine-driven hydraulic pump for an aircraft, having a first and a second pump unit which each comprise an adjustable swash plate and a piston assembly coupled with said swash plate and driven by a pump shaft, a control device for adjust...
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JP2011506186A |
A fuel cell system module for use in an aircraft includes at least one fuel cell system component. The fuel cell system module is connectable modularly to a fuselage section of the aircraft. A housing element of the fuel cell system modu...
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JP2011506185A |
An aircraft cooling system (10) comprises a cooling element (12), which comprises a housing (14), a cooling air inlet (18) formed in the housing (14) and a plurality of heat exchangers (32, 34, 36, 38), which are disposed on lateral surf...
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JP2011506184A |
Device for mechanically decoupled retention of components perfused by hot gas in an aircraft, with a coupling member for coupling to a component emitting hot gas and to a component accepting hot gas, with a holder, with a flange, and wit...
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JP2011504832A |
A flight management verification apparatus adapted to verify at least one flight management, wherein the flight management in use outputs a warning, disables an aircraft and/or inhibits the activation thereof in response to a power fail ...
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JP4596745B2 |
Process for increasing the efficiency of and reducing exhaust gases in fuel cell systems comprises increasing the oxygen amount of the air introduced for fuel cells operating with atmospheric oxygen on the cathode side and/or the hydroge...
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JPWO2009025307A1 |
An aircraft equipped with an engine, a storage battery for starting the engine, and a charge control circuit for the storage battery integrated with the storage battery.
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JP4564024B2 |
The architecture has an electric power distribution unit (710) with an electric power calibrating unit that is in the shape of a controlled inverter (711), where the inverter serves to calibrate the electric power provided from a power b...
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JP4510634B2 |
Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet eng...
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JP2010159050A |
To provide an aircraft power supply for providing DC power with improved power quality characteristics to an aircraft. According to one embodiment, the aircraft power supply includes an input filter, a step-down transformer, one or more ...
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JP2010523879A |
A turbine engine for a helicopter, including a gas generator and a free turbine driven in rotation by the gas flow generated by the gas generator is disclosed. The turbine engine further includes a motor/generator coupled to a shaft of t...
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JP4495117B2 |
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JP2010521375A |
A power regulator and a process regulator, or a power regulating device for regulating hybrid energy sources are provided for an aircraft. The power regulator and process regulator is equipped such that the requirement of a required mean...
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JP4484709B2 |
A device for producing water on board an aircraft includes at least one high temperature fuel cell entirely or partially integrated into a combustion chamber arrangement of a gas turbine aircraft engine. The combination of at least one f...
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JP2010516025A |
A fuel supply unit (10) for a fuel cell system which is in particular suitable for use in an aircraft comprises a fuel tank (12) and a feed line (14), which connects the fuel tank (12) to an inlet (16) of a fuel cell (18). A tank isolati...
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JP4459280B2 |
The invention is a starting and generating apparatus for an engine, including: a rotator configured to be used as a generator driven by an engine as well as used as a starter motor for starting the engine; a power transmission mechanism ...
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JP4444538B2 |
A power switching device in an electrical power distribution system on board a helicopter. There is a power switching device that switches on or off the power flow from a main distributor to the consumer. This switching device comprises ...
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JP2009538776A |
The arrangement (1) has a receiving region (4) for receiving a component e.g. electric line, of a line system (2). The region is accessible in some sections from outside a fuselage (3) for installation and/or maintenance of the line syst...
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JP4300682B2 |
To provide a traveling body with the improved energy efficiency in starting a propulsion engine or in the air-conditioning system in an aircraft. An auxiliary power unit of the aircraft as the traveling body comprises a power source unit...
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JP2009509835A |
The system (100) has a fuel cell (101) and energy storage such as a condenser (103). The fuel cell is coupled with the condenser by an electrically conductive connection (104) such that the condenser is recharged by the fuel cell. An inv...
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JP4198881B2 |
The need for engine bleed air in a cabin pressurizing/ventilation ECS system for aircraft is avoided in a construction including a pressurizable aircraft cabin (10) having a cabin air inlet (20) and a cabin air outlet (22). The system in...
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JP2008526620A |
The device has a power capacitor (10) to store power in an electric field, and a power supply device (4) to supply power to the capacitor. A power transfer device (12) withdraws additional power from the capacitor based on the power supp...
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JP2008518828A |
The present invention is directed to a distributed active flow control ("DAFC") system that maintains attached airflow over a highly cambered airfoil employed by an aircraft or other similar applications. The DAFC system includes a prima...
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JP2008127013A |
To provide a power supply system for an aircraft in which an engine section of the aircraft has sufficient electric power utilizable for supplying electric power to an engine and a current consumer build into the peripheral part of the e...
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JP2008114838A |
To provide an auxiliary power unit assembly (10) of an embodiment of the technology described in this specification.The auxiliary power unit assembly (10) comprises an auxiliary power unit installable in an aircraft (18) having a cabin (...
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JP2008080934A |
To provide a taking-in port door control system for an auxiliary power unit.The auxiliary power unit (APU) (100) is provided with a control device for controlling a position of an APU taking-in port door (138) at starting action of the A...
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