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Matches 101 - 150 out of 785

Document Document Title
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...  
WO/2014/158240A2
A control for a hybrid turbo electric aero-propulsion system prioritizes and optimizes the operating parameters, according to a desired optimization objective, for and across a number of different control optimization subsystems of the h...  
WO/2014/149101A3
An aircraft 1 is provided with a gas turbine engine 20 having a plurality of shafts. A first output shaft 32 provides power to an electrical machine 40 and a propeller 50, while a second output shaft 33 provides power to a refrigerant co...  
WO/2014/143273A3
A power-producing device, such as a ram air turbine, includes a controller (30) that is used to control operation of a turbine (20) of the power-producing device. The controller (30) uses an input based on an airspeed of the aircraft as ...  
WO/2014/137422A1
An aircraft, comprising: a wing; a fuselage coupled to the wing; an engine (34) coupled to at least one of the fuselage and the wing; an electrical load (20) associated with the aircraft during flight operations; a generator (32) coupled...  
WO/2014/135938A1
A drain for expelling fluids from an interior of an aircraft to an exterior of the aircraft, the drain including a drain tube disposed at the interior of the aircraft having a first end disposed in fluid communication with an aircraft eq...  
WO/2014/130124A3
A system in one embodiment includes a detection unit (116), a boil- off auxiliary power unit (140), and a controller (190). The detection unit is configured to detect a characteristic of a boil-off gas stream (123) from a cryotank (110) ...  
WO/2014/118454A1
A method and system for supplying an aircraft with electrical power, said aircraft being provided with a plurality of loads (C1-C4) to be powered, said power supply system comprising a plurality of power sources (S1, S2, S3) and an onboa...  
WO/2014/118458A1
The invention concerns a structure (3) for providing emergency electric power to an aircraft (1) comprising a pressurized cabin (10), at least one main engine and an auxiliary power unit (APU), the structure being designed to provide ele...  
WO/2014/113444A3
A supplemental thrust system for an airplane comprising a submerged inlet duct, a diffuser section in communication with the inlet duct, and a duct outlet in communication with the diffuser section, an outlet nozzle in communication with...  
WO/2014/111861A1
Disclosed is an aircraft resource management system. The system may include at least one fuel cell cluster having at least one fuel cell system configured to receive and convert a hydrogen input comprising hydrogen and an oxygen input co...  
WO/2014/106712A1
A method for managing an electric power network (1) of an aircraft, the power network (1) comprising at least one distribution bus arranged to supply electrical loads, at least one generator (G1, G2) of a propulsion engine of the aircraf...  
WO/2014/105334A1
An electrical power system for an aircraft including a turbine engine (101) coupled to the aircraft (5) and providing propulsive thrust and emitting heat during operation to define a high temperature source, a cryogenic fuel system (12) ...  
WO/2014/099182A1
According to one embodiment of the present disclosure, an exhaust apparatus for an auxiliary power unit is disclosed. The exhaust apparatus may include an exhaust housing including a perforated body surrounding an exhaust airflow of the ...  
WO/2014/082719A1
The invention relates particularly to an energy unit (1) for producing a process material on board a vehicle, comprising a fuel cell unit (2) with at least one fuel cell (3) and a mobile storage unit (5), designed to be separate from the...  
WO/2014/070640A1
An auxiliary power unit mounting system according to an exemplary aspect of the present disclosure includes, among other things, a plurality of linkages to support an auxiliary power unit, and a redundant mount to selectively support sai...  
WO/2014/070545A1
An air vehicle power and thermal management system (10) includes an aircraft controller (20) structured to distribute power provided by a gas turbine engine (36) between a cooling system (22) and an electrically powered load (14). The co...  
WO/2014/046713A1
A gas turbine engine includes a gearbox. The gearbox includes a housing at a forward part of a core compartment of a gas turbine engine. A plurality of accessory drives are each configured to rotatably couple the gas turbine engine acces...  
WO/2014/041291A1
The invention relates to a method for supplying non-propulsive power of an aircraft, comprising driving a shaft (13) of a system (1) for controlling the environment of the aircraft by a combination of energy sources selected from: an aux...  
WO/2014/037678A1
The invention relates to a method of manufacturing a stiffened panel (10) comprising a skin (11) and at least one substantially elongate stiffener (12) said stiffener comprising a longitudinal groove (13) forming a cavity (15), said pane...  
WO/2014/037650A1
The invention relates to an accessory drive gearbox for an aircraft turbine engine, said gearbox (140) comprising a box (42), a linkage (115) for controlling flaps of the aircraft, which linkage is designed to slide axially inside said g...  
WO/2014/016492A1
The invention relates to an emergency power supply device (3) for an aircraft (1), characterised in that it comprises at least one air intake duct (5) designed to receive a relative airflow V (during the flight of the aircraft), a turbin...  
WO/2014/016708A3
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...  
WO/2014/016708A2
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...  
WO/2014/001683A1
The invention aims to optimise all of the engine power available on a helicopter provided with an auxiliary engine by allowing that auxiliary engine to provide non-propulsive and/or propulsive energy during flight. For this purpose, this...  
WO/2014/001726A1
The present invention relates to a thrust-reversal device for an aircraft which includes at least two thrust reversers including a cowl which is movable between a closed position and an open position, actuated by at least one actuator (5...  
WO/2013/180982A1
An auxiliary power unit is composed of a gas turbine engine, a gearbox, and a gearbox driven generator. A mount bracket is mechanically attached to the gearbox. The bracket is for connecting to an aircraft strut system. The aircraft stru...  
WO/2013/180980A1
An auxiliary power unit has a gas turbine engine, a generator, and a gear box. A mount bracket is mechanically attached to the gear box. The bracket is for connecting to a plurality of struts. The struts are for connecting to an aircraft...  
WO/2013/167837A2
System for control and electric power supply of at least one helicopter motor/generator comprising a first DC/AC converter (30) intended to provide selectively, according to the respective positions of contactors (320, 322, 324, 326, 328...  
WO/2013/151690A1
Embodiments of the present invention relate generally to oxygen/air supply systems and methods for use with fuel cell system applications on-board passenger transportation vehicles, such as aircraft or other aerospace vehicles, ground ve...  
WO/2013/144479A1
Device (210) for supplying electrical power to an aircraft on the ground, comprising two electric generator (216, 218) driven by an auxiliary power unit (220), characterized in that the first generator is connected by connection/disconne...  
WO/2013/136286A3
Described are power management systems having at least one fuel cell system, a power distribution unit, at least one galley insert, a galley network controller, a control panel, and/or at least one battery pack. The power management syst...  
WO/2013/121139A3
The device for supplying air to an auxiliary power unit (GAP) of an aircraft, said auxiliary power unit comprising a diesel engine (M) coupled to a turbocharger (TC), the said turbocharger comprising at least one first air inlet (AIR_CAB...  
WO/2013/114058A1
The aim of the invention is to prevent the backflow of hot primary air into the peripheral opening formed between the nozzle and the ejector of the exhaust stream of a gas turbine. For this purpose, according to the invention, said perip...  
WO/2013/087051A1
The invention relates to an aircraft comprising an engine (44) having a compressor and a bleed air device (22) for providing bleed air from the engine (44), a fuel tank (24) for a fuel, at least one fuel cell (4, 6), a reactor (12) for c...  
WO/2013/076434A3
With a view to optimizing the resources needed to continue the flight upon the loss of at least one main engine, the invention seeks to unburden the propulsion system that has remained operative of all or some of the non-propulsive energ...  
WO/2013/076434A2
With a view to optimizing the resources needed to continue the flight upon the loss of at least one main engine, the invention seeks to unburden the propulsion system that has remained operative of all or some of the non-propulsive energ...  
WO/2013/072603A1
The invention relates to the optimised recovery of energy in an aircraft, at altitude and on the ground, using a single architecture. To this end, the invention aims to recover thermal energy from the exhaust. An architecture for the rec...  
WO/2013/017789A2
The invention relates to a device (210) for supplying an aircraft on the ground with electricity, comprising two electric generators (216, 218) driven by an auxiliary power unit (220), characterized in that the first generator is connect...  

Matches 101 - 150 out of 785