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Matches 51 - 100 out of 750

Document Document Title
WO/2016/203766A1
A first DC power supply unit (12A) of a DC stabilized power supply system is composed of at least a generator (42) and a PWM converter (20). A second DC power supply unit (13A) of the DC stabilized power supply system is composed of at l...  
WO/2016/201567A1
A compound cycle engine having at least one rotary unit defining an internal combustion engine, a first stage turbine in proximity of each unit, and a turbocharger is discussed. The exhaust port of each rotary unit is in fluid communicat...  
WO/2016/200601A1
A system and method for improved efficiency of an integrated power and cooling unit, IPCU (100), of an aircraft is disclosed. The IPCU (100) comprises a compressor (104), a starter/generator (106) and at least a cooling turbine (102), al...  
WO/2016/181420A1
A mount mechanism (3) for mounting an accessory gearbox (11) to the engine case of an aircraft engine comprises: a pair of first brackets (4) affixed to either the engine case or the accessory gearbox (11) and located at a distance from ...  
WO/2016/168261A1
Devices for producing vacuum using the Venturi effect and systems, such as internal combustion engine systems, including the same are disclosed. The devices include a housing defining a suction chamber, a motive passageway converging tow...  
WO/2016/156393A1
An aircraft (2) having at least one thrust providing jet engine (4, 6) and a fuselage with an integrated pressurized cabin comprises an environmental control system (16) comprising at least one pneumatic air cycle air conditioning unit (...  
WO/2016/154556A1
A flight controller system includes an electronic speed control throttle input from which an anticipated electrical power demand is determined. The flight controller system includes a controller that determines a throttle input for a gen...  
WO/2016/148870A1
An airborne wind turbine system is provided including an aerial vehicle having a fuselage, an electrically conductive tether having a first end secured to the aerial vehicle and a second end secured to a rotatable drum positioned on a to...  
WO/2016/143331A1
A power generating device for aircraft is provided with: an input shaft by which the driving force of the engine is transmitted; a transmission that is arranged in parallel with the input shaft; a generator that is arranged in parallel w...  
WO/2016/143330A1
A toroidal continuously variable transmission is provided with: an input disc and output disc arranged facing each other; a power roller held so as to be capable of tilting between the input disc and output disc, the power roller transmi...  
WO/2016/138173A1
Methods of manufacturing and operating a solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to...  
WO/2016/138139A1
A solar powered aircraft having segmented wings that can be reconfigured during flight to optimize collection of solar energy are described. The aircraft have rigid construction that is resistant to inclement weather and is configured to...  
WO/2016/133502A1
An aircraft starting and generating system includes a starter/ generator and an inverter/converter/controller (200) that is connected to the starter/generator and that generates AC power to drive the starter/generator in a start mode for...  
WO/2016/116902A1
Embodiments of the present disclosure relate generally to the use of the fuel cell systems on board aircraft and other passenger transportation vehicles and to methods of using heat, air, and water generated by such fuel cell systems. Th...  
WO/2016/107944A1
Fuselage rear end of an aircraft, comprising: - a structural part (1) comprising a skin and longitudinal (30) and transversal reinforcing members (31, 32), and - a fairing (5). The structural part (1) longitudinally spans over the whole ...  
WO/2016/107943A1
A suspension system for an aircraft auxiliary power unit located in a fuselage structure, the system comprising: - struts (10), - auxiliary power unit attachment brackets (51, 52) for connecting the strut (10) to the auxiliary power unit...  
WO/2016/105638A2
A battery containment pod including a body formed of a lightweight material. The body has an aerodynamic exterior shape and an interior cavity formed in the lightweight mate-rial, the size and shape of the interior cavity designed to acc...  
WO/2016/105638A3
A battery containment pod including a body formed of a lightweight material. The body has an aerodynamic exterior shape and an interior cavity formed in the lightweight mate-rial, the size and shape of the interior cavity designed to acc...  
WO/2016/053746A1
A transportable ground station for a UAV includes a container in which the UAV may be transported and housed. The container includes a wireless or contact-based recharging station that recharges the UAV's batteries or other power sources...  
WO/2016/046477A1
The invention relates to an assembly (1) comprising a fuel cell (3) disposed in a casing (2), the fuel cell (3) comprising an anode (4) equipped with an intake (41) and an anode outlet (42), a cathode (5) equipped with an oxygen intake (...  
WO/2015/195856A1
A system for providing regenerative power for an aircraft to sustain flight includes multiple energy cells disposed within the aircraft, the energy cells being configured to supply power to a propulsion motor and electronics of the aircr...  
WO/2015/128533A1
The invention relates to a device consisting of a base (19) having a turbine (1) that is protected and partially concealed by a cover (15), and also includes an image-recording element (16), which is a camera in the present preferred emb...  
WO/2015/126489A3
An exhaust section for an aircraft gas turbine engine includes an exhaust nozzle in a downstream serial flow relationship with the gas turbine engine having a fan section, a compressor section, a combustion section, a turbine section, an...  
WO/2015/104487A1
The invention relates to a system (1) for generating electrical energy, pertaining to an aircraft, comprising: a primary energy source (P), an auxiliary electrical energy source (APU), and an emergency electrical energy source (EPU), cha...  
WO/2015/092207A1
The invention relates to an assembly including a structure (2) and a tubular element (6), isostatically mounted in the structure (2), said tubular element (6) comprising a first end (7) connected by at least four connecting rods (10a - 1...  
WO/2015/082854A1
The invention relates to a method for mounting an engine module (1) in a mount comprising a first structure (3) and a second structure (2) that is offset relative to the first structure (3), which method is intended to position at least ...  
WO/2015/079155A1
The invention relates to a system (2) for generating non-propulsive energy in an aircraft, including: an auxiliary power unit (20) including a gas turbine (21) and a fuel cell (22); a pathway (23) for the intake of outside air into the a...  
WO/2015/075538A1
A moving body is capable of traveling on the ground and flying. The moving body includes a wheel for ground travel, a rotary vane, an engine, a first motor generator, a second motor generator, and a battery. The engine is connected to th...  
WO/2015/067239A1
The invention relates to an airplane comprising a fuel cell device (16) which can be operated with hydrogen from a hydrogen tank (22) and with oxygen drawn from the surrounding air. The airplane further comprises a superconducting magnet...  
WO/2015/063414A1
The invention concerns a method for generating auxiliary power in an aircraft, comprising the step consisting of: starting up an auxiliary power unit (6) of the aircraft by supplying compressed air to the auxiliary power unit (6) from a ...  
WO/2015/055951A1
The invention relates to a device for protecting against short-circuits upstream of an electrical power supply module (.1,60, 160'), comprising an inlet filter with at least one capacitor (106 to 108, 106' to 108') and an inductance (104...  
WO/2015/053900A1
A plurality of remote module equipment centers (410) distributed throughout a vehicle (10) to aggregate sensor and control information into localized areas of the vehicle (10); the remote module equipment centers (410) provide power and ...  
WO/2015/053902A1
Distributed electronic protections and control architecture enabling simultaneous fault clearance without conflicting fault isolation logic. A plurality of modular equipment centers (MECs) is spatially distributed throughout a vehicle to...  
WO/2015/052458A1
A method (100) of diagnosing an auxiliary power unit (10) fault in an aircraft (50) having an auxiliary power unit and multiple sensors related to the auxiliary power unit, components thereof, and systems related thereto, including recei...  
WO/2015/053903A3
A plurality of modular equipment centers (MECs) spatially distributed throughout a vehicle servicing equipment loads. Each MEC independently provides localized power and communication to service the equipment loads. A zone of electrical ...  
WO/2015/050601A3
A fuel system for a gas turbine engine comprises an injector disposed to inject fuel and air into a combustor of the gas turbine engine. In a first embodiment, the fuel system further comprises an air separation module configured to supp...  
WO/2015/050601A2
A fuel system for a gas turbine engine comprises an injector disposed to inject fuel and air into a combustor of the gas turbine engine. In a first embodiment, the fuel system further comprises an air separation module configured to supp...  
WO/2015/026433A1
A thermal energy harvester and power conversion system employs a bleed air duct (16) containing the flow of high temperature air from an engine. A lower temperature air source is included with an energy conversion device (38) having a ho...  
WO/2015/019026A1
An autonomous electrical energy production facility, designed for a propulsion nacelle of an aircraft comprising an electric circuit comprising actuators (8, 28), characterised in that it comprises means (2) for storing electrical energy...  
WO/2015/011664A3
Embodiments of the present invention provide a single coolant loop (40) that can be used for cooling at least two systems (100, 26) that are generally operable at two different temperatures. Rather than providing two separate cooling loo...  
WO/2014/207236A1
The invention relates to an aircraft structure (10), in particular the fuselage, nacelles or wings, comprising, over all or part of an outer surface (21) that may undergo lightning impacts, a layer of flexible polymer (30), a photovoltai...  
WO/2014/204549A3
Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a method to harvest renewable energy includes providing an aircraft suitable for untethered flight in an open airspace and an airborne kinetic en...  
WO/2014/182616A3
Embodiments are directed to selecting, by a computing device comprising a processor, the size of at least one prime mover associated with an aircraft to satisfy a baseline power requirement for operation of the aircraft during a steady s...  
WO/2014/182519A3
A gas turbine engine inlet door control system includes an actuator, an engine controller and a door controller. The actuator opens and closes an inlet door of a gas turbine engine. The engine controller determines an intermediate door p...  
WO/2014/178503A1
A solar airplane with solar cell modules mounted in the wings includes: a first solar cell module arranged in the main wings or tail wings for receiving the solar energy directly from the sun; a second solar cell module arranged in the m...  
WO/2014/177817A1
Electrical power distribution assembly for an aircraft comprising an electrical switching device (620) to be placed in a Karman fairing (K) of the aircraft.  
WO/2014/174207A1
The present invention pertains to a DC electrical generation system for an aircraft propelled by a turbine engine, such as a turbojet, comprising at least one electrical energy storage capacity (BAT 1, BAT 2), at least one generator (G1,...  
WO/2014/175849A1
The invention relates to engine construction, and specifically to structural elements of aviation engines, and more specifically to a system for increasing the efficiency and controllability of an aviation drive of an aircraft. The syste...  
WO/2014/162092A1
The invention concerns a system for generating electrical energy (20) for an aircraft (10) comprising an aerodynamic fairing (21) enclosing at least one turbine (22) housed in the front portion (21a) of the fairing (21) and an electric e...  
WO/2014/165502A1
Methods and apparatus to harvest renewable energy are provided herein. In some embodiments, a wind-powered aircraft (100) includes an airframe (110, 120, 130) suitable for untethered flight in an open airspace; and an airborne kinetic en...  

Matches 51 - 100 out of 750