Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 501 - 550 out of 865

Document Document Title
JP6170370B2
To properly execute load shedding in an aircraft to maintain power supply to more devices. A method of load shedding includes a failure detection step of detecting a failure in a generator, and a load-shedding step. The load-shedding ste...  
JP6166184B2
Vehicles, systems, and methods are disclosed for providing and directing first power, such as vehicle generator power, and alternate sources of power. In a particular embodiment, a vehicle includes a power distribution grid that includes...  
JP2016533955A5  
JP2017122452A
To provide an aircraft engine and an electric taxiing system which conduct taxiing without operating a core gas turbine engine by driving a fan assembly with the electric taxiing system during taxiing.An aircraft engine (10) includes a c...  
JP6159073B2
Disclosed herein is a method of providing electrical power to an aircraft. The method comprises selectively sourcing power from a plurality of power sources. The power sources comprise one or more generators driven by an engine, and at l...  
JP6148324B2
A device for supplying electrical power to an aircraft on the ground, including two electric generators driven by an auxiliary power unit. The first generator is connected by a connection/disconnection mechanism to an aircraft network an...  
JP2017100568A
To effectively use regenerative electric power of an electric motor generated when using the electric motor that is used as a power source in taxiing and running in take-off of an aircraft, as a braking source in landing.An electrically-...  
JP2017095095A
To provide aircraft fuel storage systems which provide safe, efficient and economical storage of cryogenic fuels such as liquefied natural gas (LNG) in combination with other fuel storage systems aboard the aircraft.A cryogenic fuel stor...  
JP2017514057A
The present invention is the structure of the propulsion system of a frequent occurrence helicopter provided with the turboshaft engine (1, 2) connected to the power transfer gearbox (3), Hybrid form turboshaft engine (1) which has the c...  
JP2017512697A
Module 40 for the present invention relating to a method and a device for comprehensive management by which a power network of an airplane provided with a plurality of power units was optimized, and choosing at least one optimization tar...  
JP2017512698A
A rapid revitalization system of a turbine engine of an airplane is provided with electric machinery 60 by which direct-current electric supply is carried out from electric power supply network 10 inside the plane. Switch 50 with which t...  
JP6134326B2
A method and architecture for recovery of energy in an aircraft, both at altitude and on the ground, and recovering thermal energy from an exhaust. An architecture for recovery of energy includes an auxiliary power unit APU including an ...  
JP2017081559A
To provide an aircraft system using fuel cells with capability to manage heat generated during fuel cell operation.An aircraft system 5 is disclosed including: a fuel storage system 10 comprising a first fuel tank 21 capable of storing a...  
JP2016525971A5  
JP6125235B2
A power generation system onboard an aircraft includes a fuel cell module configured to produce heat. A loop heat pipe module is coupled to the fuel cell module. The loop heat pipe module includes a first fluid that absorbs the heat from...  
JP6124913B2
A method to optimize resources needed to continue flight if at least one main engine is lost, by relieving a propulsion system that has remained operative of all or some of non-propulsive energy demands, by additional generation of non-p...  
JP2017075890A
To simply and inexpensively detect an arc occurring in a wire cable in an aircraft.A wire arc generation detector for detecting an arc occurring in a wire cable in an aircraft includes: a thin-line-shaped detection unit (thin-line conduc...  
JP2017510746A
The present invention is provided with the turboshaft engine (1, 2) connected to the power transfer gearbox (3), It has during a flight a direct-current-low-voltage network (7) on a plane supplied to the apparatus of a helicopter, Hybrid...  
JP2017509485A
The flight robot can put in in a range, without needing to transpose the big arrangement interval of a Slide side or a curved surface manually. Human necessity decreases by this and it becomes possible to improve a big field, for example...  
JP6110648B2
A direct current (DC) power distribution system 18 is provided for an aircraft 10. The system 18 includes a DC system bus 20 configured to carry electrical power from a source of electrical power to a plurality of electrical loads 16. Th...  
JP6110588B2
A power distribution system which may be provided in an aircraft for example is described. The power distribution system has a power distribution bus 110 and a plurality of localised voltage converters 120, each supplied by the power dis...  
JP2017062025A
To solve a problem on difficulty in management of a use level of each pump in a plurality of pump systems to prevent increase of usage of a part of the pumps to the other pumps, and decrease of related life cycle.A method includes recept...  
JP2017063595A
To provide a power generation system supplying electric power for an auxiliary system, using an existing thermal capacitor in a transporter.The present invention provides electric power for an auxiliary system 54 in a transporter, using ...  
JP2016515485A5  
JP2017507055A
[Subject] It is providing a method and a system which manage power generation of aviation vehicles which operates for side wind Flight . [Means for Solution] A method and a system given in book specification are related with power genera...  
JPWO2015064767A1
In a vertical climb, a slanting rise, perpendicular descent, slanting descent, level flight, and an air stop (hovering), with one-sheet wings, a large-sized braid, and the big rudder of one sheet, it is affected by the air current from t...  
JP2017047889A
To provide RAT systems configured to include a smaller generator operating with a higher power density or efficiency and at a lower operating temperature than a conventional sealed RAT system.A ram air turbine system includes a rotatable...  
JP6080171B2  
JP2017027719A
To suppress reduction of power generation performance while suppressing an increase in volume and weight.A jet engine 21 comprises: a high-pressure compressor 28 which compresses gas; a combustor 32 which burns fuel by the gas that has b...  
JP2017502629A
A plurality of remote module type device centers (410) are distributed on the whole transport plane (10) in order to summarize a sensor and control information in area where a transport plane (10) was localized. A remote module type devi...  
JP6057914B2
A module converting voltage between a high-voltage electrical network and at least one energy storage element an aircraft, the conversion module configured to reversibly convert between a DC voltage of the high-voltage electrical network...  
JP6057908B2
A method and architecture processing electrical energy regenerated from an aircraft, to address drawbacks posed by customary solutions for dissipating low energy of resistors, conventionally ceramics, which require a significant volume o...  
JP2017005944A
To provide a DC stabilizing power source system that restricts large-sizing of a power source or the like in a DC-main electric system and that is able to absorb electric power fluctuation satisfactorily.A first DC power source part 12A ...  
JP2016506467A5  
JP2016539051A
It is the method of controlling an electric power supply to a power system of an airplane provided with a plurality of power consumption part articles, and is a method including supplying electric power to a power system provided with a ...  
JP2016539609A
The electric power electricity distribution systems for airplanes are at least one DC power supply, and 1st DC electric power power distribution Buss and 2nd DC electric power power distribution Buss, Thailand Buss who combines at least ...  
JP2016539608A
In distributed electronic protection and control architecture, defective removal can be performed simultaneously, without opposing defective separation logic. A plurality of modular device centers (MECs) are spatially distributed by the ...  
JP6043322B2
A constant frequency starter/generator for a turbine engine includes a first inverter/converter, a second inverter/converter, a DC link electrically connecting the first inverter/converter to the second inverter/converter, and an electri...  
JP2014091514A5  
JP2016536191A
An auxiliary power unit (10), the auxiliary power unit (10), a component of that, And it is the method (100) of diagnosing an auxiliary power unit (10) obstacle in an airplane (50) which has a plurality of sensors related to a system rel...  
JP2016535579A
An electric power system for airplanes has a plurality of power consumption components, calculates the transitional electric power amount required with larger some of the power consumption components than the average power amount require...  
JP2014078227A5  
JP2016533955A
A system of thermal energy acquisition and electric energy conversion using a Extraction duct containing a flow of high temperature air from an engine is provided. Air supply of a lower temperature is contained with a low-temperature int...  
JP6012734B2  
JP6005659B2
Disclosed are methods, systems and apparatuses for harvesting vibrational energy from vehicles, as well as methods for locating vibrational energy on a vehicle. One harvesting apparatus comprises a vibrational energy harvester coupled to...  
JP2016531383A
The present invention is a hybrid interrupter member for electric circuits (100; 500), an interrupter member is provided with electrostatic interrupter parts (101; 501) and electric machinery interrupter parts, and it is an interrupter m...  
JP2016531390A
The embodiment of the present invention provides the single refrigerant loop (40) which can be used in order to cool at least two systems (100, 26) which can operate at two different temperature generally. Two separated refrigerant loops...  
JP2016166642A
To efficiently manufacture an assembly obtained by combining a power roller, a trunnion, and a beam of a toroidal continuously variable transmission.A toroidal continuously variable transmission includes an input disc and an output disc ...  
JP2016165950A
To provide a power generation device for an aircraft, that is compact and is small in overhang moment.A power generation device 11 for an aircraft comprises an input shaft 14 to which driving force of an engine is transmitted, a transmis...  
JP5986571B2
An aircraft power distribution network comprising first and second galvanically isolated power bus bars, and first and second remote data concentrators (RDCs), each RDC having an input/output interface (I/O) and a power supply, the first...  

Matches 501 - 550 out of 865