Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 101 - 150 out of 744

Document Document Title
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...  
WO/2013/002862A3
. A submerged ram air turbine generating system (10) adapted for use in a pod (12) mounted to the wing of an aircraft comprises a subĀ¬ merged inlet (26) extending substantially entirely around the outer surface of the pod housing (14), ...  
WO/2013/002862A2
A submerged ram air turbine generating system adapted for use in a pod mounted to the wing of an aircraft comprises a submerged inlet extending substantially entirely around the outer surface of the pod housing, a stator in the form of a...  
WO/2012/161929A1
A ram air turbine (32) comprises a turbine housing (72) which mounts a number of circumferentially spaced turbine blades (104) that function predominantly as impulse turbine blades and a number of splitters (106), each located in between...  
WO/2012/137843A1
A generator apparatus (1) capable of preventing an increase in the frontal area of an aircraft engine is provided with: a transmission (22) connected to a rotating shaft of the engine; a generator (34) driven by output from the transmiss...  
WO/2012/137844A1
Provided is a compact aircraft engine obtained by configuring the aircraft engine so that an accessory can be directly supported without the use of an accessory gear box. An aircraft engine (E) is provided with: a take-off shaft (11) whi...  
WO/2012/130458A3
The present invention relates to an aircraft fuel cell system (1) comprising a fuel tank (2), a reactor (3) for generating hydrogen gas from a fuel, heating apparatus (4) and a fuel cell (5), wherein the reactor can process a synthetic f...  
WO/2012/100646A1
An electromagnetic air flow pressure-relief and propelling device comprises a lifting flat plate (1), a pair of electrodes (2), a magnet (3), a laser source (4) and several laser reflectors (5). The electrodes (2) are disposed on two sid...  
WO/2012/101313A3
The invention relates to a device (1) for draining the APU of an aircraft, which device is flexible and fire resistant and which comprises a bellows (2) that receives losses of fluid from the APU, a drain pipe (3) that transfers the flui...  
WO/2012/094041A1
Disclosed are methods, systems and apparatuses for harvesting vibrational energy from vehicles, as well as methods for locating vibrational energy on a vehicle. One harvesting apparatus comprises a vibrational energy harvester coupled to...  
WO/2012/091828A3
An inlet for a ram air turbine ( 200 ). The inlet is positioned forward of a turbine shaft, which is configured to rotate about a portion of an object ( 100 ). The inlet has a fixed geometry that chokes airflow through the inlet to preve...  
WO/2012/079874A3
A fuel cell system (2) comprises a fuel cell (6) having a housing (4) that encases the fuel cell (6), a supply line (14) for a fuel cell fuel, and an exhaust gas line (10) for fuel-cell exhaust gas. In this arrangement the supply line (1...  
WO/2012/081926A3
The present invention relates to a long-endurance airplane using wind power energy. The objective of the present invention is to provide a long-endurance airplane using wind power energy as a power source. The long-endurance airplane usi...  
WO/2012/080827A3
A matrix assembly is provided for an electrical system such as, for example, a power distribution unit for an aircraft. The electrical system includes an enclosure and a number of current carrying components such as, for example, electri...  
WO/2012/081926A2
The present invention relates to a long-endurance airplane using wind power energy. The objective of the present invention is to provide a long-endurance airplane using wind power energy as a power source. The long-endurance airplane usi...  

Matches 101 - 150 out of 744