| Document |
Document Title |
|
JP6378209B2 |
A method and a system for supplying electrical energy to an aircraft that is equipped with a plurality of loads to be powered, said power supply system comprising a plurality of power sources and an on-board energy management module, the...
|
|
JP6371068B2 |
An electric wire structure keeps down the weight and improves the ease of routing, as well as allows an existing electric wire to be easily provided with measures against electromagnetic waves. The electric wire structure includes: a sin...
|
|
JP6363598B2 |
Embodiments of the present invention relate generally to removable storage for hydrogen networks on-board an aircraft, aerospace vehicles, or other passenger transport vehicles. They are particularly related to such vehicles that use a h...
|
|
JP6353055B2 |
A method for controlling the supply of power to a power system for an aircraft having a plurality of power-consuming components includes supplying power to the power system with a generator having a power output, determining a power requ...
|
|
JP6343243B2 |
An electric power generating device for an aircraft, which is driven by an output of an aircraft engine, comprises an input shaft to which a driving force of the engine is transmitted; a transmission arranged with the input shaft; an ele...
|
|
JP6329960B2 |
An aircraft turbomachine calculator including a parallelepiped metal casing including an electronic circuit wherein a control channel and a monitoring channel are integrated. The casing includes a first cavity wherein a first electronic ...
|
|
JP6320373B2 |
A method and configuration to optimize an entire traction system available on a helicopter including an auxiliary engine by allowing the engine to provide non-propulsive and/or propulsive power during flight. The auxiliary engine is coup...
|
|
JP6316281B2 |
An electrical control and power supply system for at least one helicopter motor/generator, the system including a first DC/AC converter selectively delivering AC electrical power to the at least one motor/generator, depending on respecti...
|
|
JP6313566B2 |
A method and apparatus for electrical power system (100) stability optimization. An electrical power system (100) comprising source elements (109) and load elements (111) is simulated to generate impedance data (328), wherein the impedan...
|
|
JP6313756B2 |
A method and architecture to optimize an entire traction system available on a helicopter by using an auxiliary engine to provide energy to equipment and accessories of the helicopter connected to the engines. Main engines and an APU uni...
|
|
JP2018509871A |
The aircraft start-up and power generation system is connected to the starter / generator to generate AC power to drive the starter / generator in start mode to start the aircraft prime mover and starter / after the prime mover is starte...
|
|
JP2018509124A |
Aircraft start-up and power generation systems include starters / generators including main machinery, exciters, and permanent magnet generators. The system is also connected to a starter / generator to generate AC power to drive the sta...
|
|
JP6302544B2 |
A method of diagnosing an auxiliary power unit fault in an aircraft having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, including receiving a sensor si...
|
|
JP6297259B2 |
The present disclosure relates to an unmanned aerial vehicle (UAV) able to harvest energy from updrafts and a method of operating an unmanned aerial vehicle. An unmanned aerial vehicle with a gliding capability comprising: a generator (1...
|
|
JP2018500234A |
Aircraft are equipped with energy output components (EOCs) that output waste energy. An energy recovery unit (ERU) is operably coupled to EOC to convert waste energy into either electrical or mechanical energy. An energy storage unit (ES...
|
|
JP6251264B2 |
An electric system of an aircraft includes a power stabilizing device connected to a primary AC bus and a secondary battery. The secondary battery has a rated voltage which allows the secondary battery to absorb regenerative power from a...
|
|
JP2017214931A |
To provide a manual starter assembly which requires small pulling force.A manual starter 108 for an engine, is equipped with a main housing 202; an output shaft 212; a spring housing 206; a spring 210; two claws 226 and 228; and first an...
|
|
JP2017532536A |
The present invention relates to locating an electrical fault (61) in an electrical circuit (50), and more particularly to an electrical fault (61) in a transmission line (60) of the electrical circuit (50). An embodiment of the present ...
|
|
JP6224869B2 |
The rapid assistance device applies to a free turbine engine of an aircraft having at least a first free turbine engine provided with a gas generator and associated with an electrical machine capable of operating both as a starter and as...
|
|
JP6216799B2 |
A device protecting an aircraft turbomachine computer against speed measurement errors, including: on a speed regulation channel: a speed sensor of a turbomachine gearbox shaft, a speed measurement circuit, and a speed regulation circuit...
|
|
JP6212483B2 |
A chain of components for transmitting electric power of an aircraft includes an auxiliary power unit (APU), main engines and end consumer systems via power networks and electronic connections controlled by a unit. The APU supplies power...
|
|
JP6208216B2 |
An emergency starter that allows responsiveness within a few seconds, without having disadvantages associated with mass and size of a back-up hydraulic or pneumatic starter. An instantaneous gas thrust of pyrotechnic type is coupled with...
|
|
JP6203822B2 |
The invention aims to form equipotential connections between the various parts of a current return network. For this purpose, the invention provides a loom having a layer of conductors coated in a leak-proof jacket. A connecting loom (30...
|
|
JP6205321B2 |
The present invention relates to a method and device for monitoring APU turbine vane fracture and rotor shaft jam. The method for monitoring APU turbine vane fracture and rotor shaft jam comprises: acquiring APU messages at multiple time...
|
|
JP6205318B2 |
The present invention relates to a method for detecting performance of the lubricant cooler in aircraft auxiliary power unit APU, comprising: acquiring APU-related messages within a time period; obtaining the operation parameters of the ...
|
|
JP6205320B2 |
|
|
JP6205322B2 |
The present invention relates to a method for detecting performance of an APU fuel assembly, comprising: obtaining APU messages at multiple time points within a time period; obtaining running parameters of the APU fuel assembly according...
|
|
JP6205319B2 |
The present invention relates to a method and device for monitoring performance of an auxiliary power unit (APU) turbine efficiency of an aircraft. The method comprises: obtaining APU messages at multiple time points within a period; obt...
|
|
JP2017154553A |
To prevent overheating of a structural member such as a pivot bulkhead opposing to the rear side of a fire-proof wall, and to maintain the structural member at equal to or lower than a permissible temperature.An aircraft includes: a fire...
|
|
JP6188836B2 |
The invention is related to an aircraft (1) with a fuselage (2) that defines at least an interior region (2a) and a drive system accommodating region (1f), said drive system accommodating region being arranged inside said fuselage (2) an...
|
|
JP6185180B2 |
Methods and systems described herein relate to power generation control for an aerial vehicle. An example method may include operating an aerial vehicle in a crosswind-flight orientation substantially along a first flight path to generat...
|
|
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...
|
|
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...
|
|
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...
|
|
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...
|
|
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 comprises a multi-engine helicopter with a turboshaft engine (1, 2) connected to a power transmission gearbox (3) and a DC low voltage on-board network (7) that supplies helicopter equipment during flight. A hybrid ...
|
|
JP2017509485A |
The flying robot can bring a large array spacing of smooth or curved surfaces into range without the need for manual transposition. This reduces human needs and allows for large aspects, such as solar power plants, to be fully automated....
|
|
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...
|
|
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 |
A solid state primary power switching network for modular equipment centers (MECs) distributing primary power throughout a vehicle. The solid state primary power switching network includes multiple primary power switch network devices (P...
|
|
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...
|
|
JP2016539051A |
A method of controlling the power supply to the power system of an aircraft equipped with a plurality of power consuming parts, that is, supplying power to a power system having a generator having a certain output and determining the pow...
|
