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Patent Searching and Data


Matches 751 - 800 out of 867

Document Document Title
JP2008532253A
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...  
JP2008529893A
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...  
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...  
JP2008521693A
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...  
JP2008132973A
To provide an auxiliary power unit installable in an aircraft having a cabin, a duct connecting the cabin to the auxiliary power unit, and an airflow control mechanism in the duct.This auxiliary power unit assembly 10 includes the auxili...  
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...  
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...  
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 (...  
JP2008514485A
The system and method for operating the electric power system of an airplane are indicated. Including the controller by which the electric power system according to one case of the operation of this invention is combined with the auxilia...  
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...  
JP4068071B2  
JP4044991B2
The system consists of a hydraulic subsystem (12) and an electrical subsystem (13), between which a bi-directional energy transfer occurs. Each subsystem contains a machine (20) whose rotary elements are mechanically coupled. The hydraul...  
JP2008014325A
To provide a method and a system for controlling a continuous variable transmission which does not cause instable control during starting.In this method for controlling the continuous variable transmission 1, the gear ratio of the contin...  
JP2007537084A
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,...  
JP2007537085A
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 ...  
JP2007297042A
To provide a power source device in which a large number of electric devices can be power-fed in an aviation engine and/or its environment. The power source device for the aircraft includes first generators (10, 10') driven by the engine...  
JP2007531855A
The gear box (30, 130) which rotates a propeller in the one direction in which it was chosen of the 1st or 2nd direction is offered. The 2nd direction is reverse to the 1st direction. A gear box has the 1st and the gear of the 2nd compos...  
JP2007246083A
To provide a structure for power distribution, reduced in weight more than the conventional structure by utilizing the advantage that specified movable elements are operated in order. In this power distribution structure especially adapt...  
JP2007218253A
To provide an aircraft auxiliary gas turbine for an aircraft which is improved and not for propulsion, and an improved method for operating this kind of engine. The aircraft auxiliary gas turbine engine (10) is not for propulsion and is ...  
JP3930413B2
To provide a system capable of supplying power and selectively supplying thrust as required to an aircraft system. This variable cycle boost propulsor system 10 has a core engine 14, a free turbine 30, a fan 34 connected to the free turb...  
JP2007510591A
Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one po...  
JP2007015423A
To provide a power supply system for an airplane 1 of lightweight construction and with a high efficiency.The power supply system S is equipped with main generators GEN1 and GEN2 driven by a propulsive engine 4 of the air plane 1, an aux...  
JP2006518683A
A system and method for an engine bleed flow-sharing control system is disclosed. For a multi-engine bleed system, one (10) of the engines is selected as the master channel (15) such that the bleed air supply pressure of the control syst...  
JP2006518297A
A fire protection apparatus for an oil cooler in an aircraft auxiliary power unit compartment adapted to at least partially cover the oil cooler to thereby at least partially block flames from directly impinging the oil cooler in the eve...  
JP3803326B2
To provide an auxiliary power device integrally formed with an engine. In the auxiliary power device integrally formed with an engine, the engine 10 has: a high pressure spool including a high pressure compressor 20 connected to a high p...  
JP3793529B2
To integrate environmental control, secondary power and emergency power. An apparatus comprises of a cooling turbine that is coupled to a first rotor of an electromechanical machine and has an input for receiving compressed air or ram ai...  
JP2006516230A
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...  
JP2006062439A
To continuously supply power to apparatuses loaded on a hot-air balloon during flight with a simple structure.The power supply of hot-air balloon for supplying power to apparatuses equipped in the hot-air balloon comprises a thermoelectr...  
JP2006504043A
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...  
JP2005256840A
To provide a method and an apparatus for operating a gas turbine engine used for aircraft propulsion and auxiliary power.An aircraft gas turbine engine assembly (10) contains at least one propelling gas turbine engine (11) equipped with ...  
JP2005507044A
A passive cooling system for an auxiliary power unit (APU) installation on an aircraft is provided. The system is for an auxiliary power unit having at least a compressor portion of a gas turbine engine and an oil cooler contained separa...  
JP2004340148A
To provide a device and a method for decomposition of propellant.The propellant 24 includes ionic salt and additional fuel. A means 42 to decompose most parts of the ionic salt is provided. A means 48 to burn the additional fuel and deco...  
JP2004324639A
To integrate environmental control, secondary power and emergency power.An apparatus comprises of a cooling turbine that is coupled to a first rotor of an electromechanical machine and has an input for receiving compressed air or ram air...  
JP2004232636A
To provide a gas turbine assembly 10 to be used in an aircraft.The gas turbine assembly 10 includes a propulsion gas turbine and an auxiliary power unit 12. The propulsion gas turbine includes a fan 14 and a core engine 11 to generate th...  
JP2004524474A
[Subject] The present invention aims exhaust gas temperature significant at offer of the whirlpool generation equipment which can decrease in number in auxiliary power unit systems, such as a jet engine. [Solution means] In the hand of c...  
JP2004211706A
To provide a device for improving the efficiency and energy output of an electric power device, and its method.The electric power device uses a fuel cell which is constructed to chemically convert combustible fuel into electrical energy....  
JP2003331877A
To provide a method for improving the efficiency and for reducing an exhaust gas in a fuel cell system.In the fuel system wherein air is fed to the negative electrode side and hydrocarbon is fed to the positive electrode side in operatio...  
JP2003304699A
To provide a small-sized light-weight power-generating apparatus which can generate a predetermined power, irrespective of the operating state of a connected prime mover.The power generating apparatus comprises a generator having a rotor...  
JP3440287B2
To provide a method and device for driving at constant rate a generator mounted in an aircraft, whereby the generator can be formed into a compact structure having high efficiency and reliability and long life. The AC generator 2 is driv...  
JP2003227412A
To provide an auxiliary power device integrally formed with an engine.In the auxiliary power device integrally formed with an engine, the engine 10 has: a high pressure spool including a high pressure compressor 20 connected to a high pr...  
JP2003523298A
A thermoelectric power generator for an aircraft including a heat source or hot air exhaust air flow (30), characterized as providing thermal energy, at least one thermoelectric module (32), including a plurality of thermoelectric elemen...  
JP2003184653A
To provide a system capable of supplying power and selectively supplying thrust as required to an aircraft system.This variable cycle boost propulsor system 10 has a core engine 14, a free turbine 30, a fan 34 connected to the free turbi...  
JP2002154490A
To provide a power switching device including an overhead operation console at least having a switching means in an airborne distribution equipment of a helicoputer for switching power from a main distributor to a power consumption devic...  
JP3270845B2
To provide a boundary layer control mechanism for a short takeoff/ landing distance plane without apprehension generating hot circulation while forming a protruded part behind a pilot seat aerodynamically approximated to an optimum shape...  
JP2001334998A
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 ...  
JP2001515825A
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...  
JP2001234999A
To provide a highly reliable axial force generating device by a simple constitution and to provide a traction transmission using it.This axial force generating mechanism 10 comprises a centrifugal force generating mechanism, a converting...  
JP2001158400A
To provide a method and device for driving at constant rate a generator mounted in an aircraft, whereby the generator can be formed into a compact structure having high efficiency and reliability and long life.The AC generator 2 is drive...  
JP2001130498A
To prevent a hazard by belly landing and a crash accident due to engine trouble. The conventional equipment is exchanged basically with new ones. This operation is performed positively.  
JP2001116499A
To secure initial power by generating electric power in its launching tube in a flying object which gyratingly flies. A self-gyration type initial generator incorporated in an object which gyratingly flies generates electric power by usi...  

Matches 751 - 800 out of 867