| Document |
Document Title |
|
JP5934326B2 |
An electrical power system for an aircraft having electrical loads and at least one jet engine with a high pressure spool and a low pressure spool, the electrical power system includes a first electrical machine driven by a first pressur...
|
|
JP5932782B2 |
An aircraft electrical supply circuit including: a power distribution network, onboard the aircraft, for electrical devices located in an engine of the aircraft or near the engine; and a power supply generator built into the engine of th...
|
|
JP5923515B2 |
A method improving acceleration efficiency of a gas generator of a gas turbine by reducing take-up of electric power, during transition phases, to conserve a sufficiently large surge margin for an operating line. The method increases acc...
|
|
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...
|
|
JP2016508466A |
The present invention relates to a structure (3) that supplies emergency power to an aircraft (1), wherein the aircraft (1) has a pressurized cabin (10), at least one main engine, and an auxiliary power unit (APU). ), And the structure i...
|
|
JP5873493B2 |
A method and system limiting specific consumption of an aircraft by matching sizing of a power supply to actual power needs of a cabin pressure control system. The method optimizes overall efficiency of energy supplied onboard an aircraf...
|
|
JP5824558B2 |
The present invention relates to built-in testing of detectors for the detection of electrical arc faults or transients, where the detector is integrated into or electrically coupled to an electrical power supply system.
|
|
JP5816202B2 |
A gas turbine engine (10) includes an accessory gearbox (60) within an engine pylon (P). The accessory components (66) may be mounted within the engine pylon (P) to save weight and space within the core nacelle (12) as well as provide a ...
|
|
JP2015531721A |
A method of supplying non-propulsive power to an aircraft, the shaft (13) of the aircraft's environmental control system (1): auxiliary power unit (4), starter / generator (18), and auxiliary air supply means ( A method that includes the...
|
|
JP2015531716A |
Aircraft electrical equipment includes an engine starter motor control unit (1) configured to provide an AC input voltage to the transformer rectifier unit (2). Preferably, the device includes a transformer rectifier unit (2) for powerin...
|
|
JP5801771B2 |
The present application discloses a method for detecting performance of an APU, comprising: obtaining EGT (Exhaust Gas Temperature), LCIT (Load Compressor Inlet Temperature), STA (Starting Time), TSR and PT, comparing respectively a diff...
|
|
JP2015120514A |
To provide a system and method to make it possible to easily and efficiently manage and analyze an electrical load from design to retirement of an electrical system, thereby minimizing costs of electrical load analyses while meeting tota...
|
|
JP2015107791A |
To provide a method of predicting an auxiliary power unit fault.A method 100 of predicting an auxiliary power unit fault in an aircraft having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components t...
|
|
JP2015514295A |
In vehicles such as aircraft, the restroom unit can be powered by the various outputs of the fuel cell system, including commonly discarded by-products. For example, but not limited to, a combination of water and / or oxygen depleted air...
|
|
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...
|
|
JP5707483B2 |
Technologies are described herein for detecting and recovering from a fire event within an aircraft. The technologies receive sensor data from a number of sensors associated with an aircraft. A determination is made as to whether the sen...
|
|
JP5705909B2 |
The present invention broadly comprises an aircraft motion control auxiliary power unit suspension system device, the aircraft motion control auxiliary power unit suspension system device comprising a first motion control nonelastomeric ...
|
|
JP2015511199A |
A device for supplying air to an auxiliary power unit (GAP) of an aircraft, said auxiliary power unit including a diesel engine (M) coupled to a turbocharger (TC), the turbocharger being a diesel engine. It is equipped with at least one ...
|
|
JP5634086B2 |
The present invention relates generally to electrical power distribution, for example, in aircraft. More particularly, according to a first aspect, the present invention relates to a power supply system 100 for power distribution to one ...
|
|
JP2014193711A |
To provide methods of accurately reading hydraulic fluid levels in tanks regardless of change in the hydraulic fluid levels during movement of the aircraft including taxi, takeoff, landing, and flight.A method 100 of monitoring hydraulic...
|
|
JP5597876B2 |
|
|
JP2014159212A |
To provide a lithium battery system for aircrafts or the like which prevents transmission of an impact to the body of the lithium battery body and does not cause ignition.A lithium battery 7 is held to the airframe or an outer case 13 wi...
|
|
JP5568129B2 |
A starting and generating system for use with an aircraft engine includes a starter/generator and an inverter/converter/controller (ICC) coupled to the starter/generator. The starter/generator is configured to start the aircraft engine i...
|
|
JP5524850B2 |
The present invention broadly comprises an aircraft motion control auxiliary power unit suspension system device, the aircraft motion control auxiliary power unit suspension system device comprising a first motion control nonelastomeric ...
|
|
JP2014513511A |
A generation method performed by a generator module of an electricity network of an aircraft, the electricity network including a power supply line powered by the generator module, a DC bus powered from the power supply line via a rectif...
|
|
JP2014091514A |
To provide a ram air turbine generator system that has a decreased number of parts and can increase reliability.A ram air turbine generator system 12 for generating electrical power when exposed to an external airstream of aircraft inclu...
|
|
JP2014078227A |
To provide a method for modeling an electrical power system of an aircraft.A method 100 of modeling an electrical power system of an aircraft comprises: among others, identifying electrical characteristics 110, mechanical characteristics...
|
|
JP5450048B2 |
An aircraft starting and generating system includes a starter/generator that includes a main machine, an exciter, and a permanent magnet generator. The system also includes an inverter/converter/controller that is connected to the starte...
|
|
JP5421216B2 |
The network (10) has a three-phase power bus (11) conveying three-phase alternating current (AC) power generated by one direct current (DC)/AC converter (12) that is powered by a DC source of an aircraft. The DC/AC converter is fitted wi...
|
|
JP5385145B2 |
A device and a method for supplying electrical power to at least one induction machine on board an aircraft. This device includes at least one CVFR type source, in which the voltage and frequency are both variable but in a constant ratio...
|
|
JP5385127B2 |
The device has air conditioning plants (ECS1-ECS4) utilized as emergency electric generators. The plants compress air coming from the exterior of an aircraft e.g. civil transport plane. Air compressors of the plants are driven by electri...
|
|
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...
|
|
JP5373596B2 |
A device and a method for emergency electricity supply on board an aircraft, able to supply a part of the aircraft's electrical power circuit. The device includes a synchronous machine with separate excitation, associated with a flywheel...
|
|
JP2013251264A |
To provide an electrical power unit that provides electrical power to an electrical component on-board an aircraft in an emergency situation.An electrical power unit provides electrical power to an electrical component 12 on-board an air...
|
|
JP2013220681A |
To provide an auxiliary power system capable of effectively using hot water produced by a fuel cell type auxiliary power supply device.An auxiliary power system has a fuel cell type auxiliary power supply device 2. Hot water X produced w...
|
|
JP5325367B2 |
An aircraft gas turbine engine assembly (10), including at least one propelling gas turbine engine (11) comprising a core engine (13) and an exhaust (32). The core engine includes at least one turbine (20) for generating thrust for the a...
|
|
JP5325411B2 |
An embodiment of the technology described herein is an auxiliary power unit assembly (10). The auxiliary power unit assembly (10) includes an auxiliary power unit being installable in an aircraft (18) having a cabin (22), a duct (28) con...
|
|
JP2013204432A |
To provide a motive power device for an aerial-to-ground vehicle which minimizes weight requiring start-up of the motive power device.A motive power device has a gas turbine 10 for flight in the air, a running motor-driven generator 26 w...
|
|
JP5298027B2 |
A system and method for switching power sources for an aircraft electric brake system is disclosed. The method removes battery power from electric brake actuator controls during flight until landing gear extension occurs. The method util...
|
|
JP5275976B2 |
A system and a method for distribution of electric power inside an aircraft. The system includes at least two systems distributing electric power from at least one power source to electric loads of the aircraft via electric and/or electr...
|
|
JP5269780B2 |
A fuel cell (10) has a compressed air inlet fed by a compressor (20) and a fuel inlet, and it produces direct current electricity. A turbine (30) receives a flow of gas under pressure from the fuel cell and is mechanically coupled to the...
|
|
JP5231149B2 |
A current control circuit (active element) is provided that is connected between a rectifier of a DC power source and a smoothing capacitor in a power frequency converter and that controls a variation in the rectified current caused by a...
|
|
JP5230636B2 |
The system has electrical distribution channels (B) e.g. three phase alternating system, for high power loads and electrical distribution channels (G1) for conventional loads e.g. fuel pump. The distribution channels are separated and ar...
|
|
JP5216146B2 |
A power generation system for integration into an aircraft system, including a secondary power supply device having a generator turbine arranged in a duct running between a forward opening and a rearward opening on the fuselage of the ai...
|
|
JP5205362B2 |
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...
|
|
JP2013517986A |
An electrically driven aircraft may include a tank for NH3 in order to provide NH3, an energy source, which generates electric energy using and converting NH3, an electrically driven propulsion system that ensures the propulsion of the a...
|
|
JP2013091487A |
To provide an electrical power generation system for an aircraft using waste heat generated by a system of an aircraft.An electrical power generation and distribution system (1) for an aircraft includes a plurality of heat sources (2, 3,...
|
|
JP2013515644A |
An aircraft including an electric starter-generator for each of turbojets, and an undercarriage including an electric motor for taxiing the aircraft, which mutualizes an electricity converter for starting and for taxiing the aircraft. A ...
|
|
JP2013082434A |
To provide a system and a device that achieve improvement of the power distribution in an aircraft.The power distribution system includes: a first wiring harness 150 connected to a power supply 120; at least one integrated switching powe...
|
|
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...
|
