Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 201 - 250 out of 864

Document Document Title
WO/2012/045864A1
An air conditioning system in an aircraft comprises at least one air cycle air-conditioning pack with a compressor comprising a bleed air outlet and with a compressed-air line connected to the bleed air connection, which compressed-air l...  
WO/2011/142844A3
Air vehicles and associated aerodynamic structures are provided which include ridged solar panels to both reduce the drag and increase the solar energy harvested by the solar panel. The air vehicle may include an airframe and a solar pan...  
WO/2012/025687A2
The invention relates to limiting the specific consumption of an aircraft by matching the sizing of the power supply to the actual power needs of the cabin pressure control system, and more generally to that of the aircraft. According to...  
WO/2012/025688A1
The aim of the invention is to remove the mechanical bleed constraints in the engines during the transient flight phases of an aircraft in order to optimize the operability of the engine assembly during said phases. To this end, a supply...  
WO/2012/012474A2
A safe, quiet, easy to control, efficient, and compact aircraft configuration is enabled through the combination of multiple vertical lift rotors, tandem wings, and forward thrust propellers. The vertical lift rotors, in combination with...  
WO/2011/157924A1
The invention relates to an aircraft engine (1) including a stator (2), a main shaft (3), a first rotor (4), a second rotor (5), a transmission mechanism (6), a first electrical apparatus supported by the first rotor and a second electri...  
WO/2011/154645A1
The invention relates to an aircraft electrical power supply circuit including: an power distribution network (17), onboard the aircraft, for electrical devices (5b) located in an engine of the aircraft or near said engine; and a power s...  
WO/2011/151160A1
The invention relates to a power supply unit for an aircraft, such as a helicopter or a fixed-wing aircraft. The power supply unit according to the invention comprises at least one power provision component for providing electrical energ...  
WO/2011/113696A3
An energy-regulating device (2) for regulating hybrid energy sources (E1, E2) for an aircraft is designed to determine an operating characteristic of an energy source (E1, E2), a requirement of a first required resource of at least one f...  
WO/2011/146021A1
The present invention relates to a yaw control and anti-spin device for fixed wing aircraft which is self -powered by means of recuperating the energy from the wingtip or wing's trailing edge vortices, which occur during flight. The same...  
WO/2011/023678A3
The invention relates to a power grid for an aircraft, and to a method for operating the power grid. The invention is particularly useful for commercial jumbo jets which comprise more and more onboard electrical apparatuses. The grid inc...  
WO/2011/089016A3
The invention relates to a self-sufficient monument in an aircraft pressure cabin which is supplied with required operating resources in a decentralized manner such that said resources are entrained in operating resource stores in the mo...  
WO/2011/113696A2
An energy-regulating device (2) for regulating hybrid energy sources (E1, E2) for an aircraft is designed to determine an operating characteristic of an energy source (E1, E2), a requirement of a first required resource of at least one f...  
WO/2011/071602A3
A device for producing electrical power. A thermoelectric device is coupled to an aircraft bleed system for generating electrical power using temperature differentials between ram air and bleed air.  
WO/2011/089196A1
The invention relates to a device and method for regulating the humidity in a fuel cell that detect a step response of the output voltage of a fuel cell when the supply to electric consumers is interrupted, determine parameters of the dy...  
WO/2011/037855A3
An aerial vehicle is configured to operate in a base fuel cell operating mode and a fuel cell boost operating mode. A method for controlling the aerial includes providing a base fuel cell upper power limit. The method further includes co...  
WO/2011/037850A3
A method for managing power flow within an aerial vehicle includes determining a fuel cell power limit and a battery energy reserve. The method further includes determining a flight operation power requirement. The method further include...  
WO/2011/072366A1
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...  
WO/2010/105744A4
The invention relates to a cooler (10) for an aircraft cooling system (100), comprising a matrix body (12) in which a plurality of coolant channels (16) are designed and extend from a first surface (18) of the matrix body (12) to a secon...  
WO/2011/051210A1
The invention relates to a fuel cell system having a device for drying gases, comprising at least one cooling body having at least one first surface and at least one removal device. The cooling body is designed to be thermally connected ...  
WO/2011/042215A1
The invention relates to a cooling system for cooling a fuel cell system (2) in a vehicle and for thermally connecting to fuel (8) in a fuel tank. This results in the fuel (8) in a fuel tank (6) being used as a heat sink having high ther...  
WO/2011/037850A2
A method for managing power flow within an aerial vehicle includes determining a fuel cell power limit and a battery energy reserve. The method further includes determining a flight operation power requirement. The method further include...  
WO/2011/037855A2
An aerial vehicle is configured to operate in a base fuel cell operating mode and a fuel cell boost operating mode. A method for controlling the aerial includes providing a base fuel cell upper power limit. The method further includes co...  
WO/2010/105744A3
The invention relates to a cooler (10) for an aircraft cooling system (100), comprising a matrix body (12) in which a plurality of coolant channels (16) are designed and extend from a first surface (18) of the matrix body (12) to a secon...  
WO/2011/023678A2
The invention relates to a power grid for an aircraft, and to a method for operating the power grid. The invention is particularly useful for commercial jumbo jets which comprise more and more onboard electrical apparatuses. The grid inc...  
WO/2010/146291A3
According to the invention, the rear portion (1) of the fuselage of said aircraft contains said fuel cell system (5), and said aircraft comprises a rear cone (2) which is removably mounted relative to said rear portion (1) of the fuselag...  
WO/2011/010033A1
The present invention relates to an electric power supply circuit (1) for a turbojet engine nacelle including at least one electric generator (2) mechanically connected to the shaft of a turbojet engine, said generator being capable of d...  
WO/2010/146291A2
According to the invention, the rear portion (1) of the fuselage of said aircraft contains said fuel cell system (5), and said aircraft comprises a rear cone (2) which is removably mounted relative to said rear portion (1) of the fuselag...  
WO/2010/136624A1
The invention comprises a skin provided with a movable fairing (1) which is supported on the skin by means of a swing hinge mechanism (7), so as to allow the opening/closing of the movable fairing (1) and access to the tail cone interior...  
WO/2010/097213A3
The invention relates to a safety power supply device (10) comprising: a channel (K) which extends along a fuselage (R) of the aircraft (F) between two openings (4; 5, 85, 95) and has a front opening (4) and a rear opening (5), a turbine...  
WO/2010/046520A3
Auxiliary power unit (APU) of an aircraft comprising a power module (1) powered by fuel (2), a gearbox (5), an electricity generator (6), and an element chosen from a compressor (4), a hydraulic pump and a combination thereof, to provide...  
WO/2010/066440A3
The invention relates to an emergency power system for an aircraft, comprising at least one fuel cell unit (FCEPS) for generating electricity. Said fuel cell unit (FCEPS) is cooled using at least one cooling cycle encompassing at least o...  
WO/2010/112645A1
The invention comprises a shell provided with a movable fairing (2) that, by means of guides (7), moves by sliding longitudinally to allow the opening/closing of the movable fairing and access to the interior of the tail cone (1). The in...  
WO/2010/080234A3
A stand-alone power generation device (10) that provides power to an auxiliary- system on an airborne platform, includes a piezoelectric energy harvesting device (11) and an energy storage unit (60), including a battery (62) and a power ...  
WO/2010/080234A2
A stand-alone power generation device that provides power to an auxiliary system on an airborne platform, includes a piezoelectric energy harvesting device and an energy storage unit, including a battery and a power conditioner. The devi...  
WO/2010/040837A3
The invention relates to a sound absorber (2) for an auxiliary engine of an aircraft comprising an inlet (46), an outlet (48), a housing (4), and a flow channel (6) which has a porous wall material and is arranged in the housing (4). An ...  
WO/2010/066440A2
The invention relates to an emergency power system for an aircraft, comprising at least one fuel cell unit for generating electricity. Said fuel cell unit is cooled using at least one cooling cycle encompassing at least one heat exchange...  
WO/2010/052338A1
The present invention provides a power distribution device for distributing power and provides a method for distributing power. The power distribution device for distributing power, in particular in an aircraft, comprises a number N1 of ...  
WO/2009/153011A4
An intersecting element (10) for connecting a first section of an aircraft supply system, which section is provided on an aircraft interior equipment component (12), to a second section of the aircraft supply system comprises a support s...  
WO/2010/046520A2
Auxiliary power unit (APU) of an aircraft comprising a power module (1) powered by fuel (2), a gearbox (5), an electricity generator (6), and an element chosen from a compressor (4), a hydraulic pump and a combination thereof, to provide...  
WO/2009/132846A3
The invention relates to an aircraft which comprises: a fuselage having a fuselage part (1), a power supply device (E), and at least two receiving devices (A) on the fuselage part (1) for fastening the power supply device (E). The invent...  
WO/2010/040837A2
The invention relates to a sound absorber (2) for an auxiliary engine of an aircraft comprising an inlet (46), an outlet (48), a housing (4), and a flow channel (6) which has a porous wall material and is arranged in the housing (4). An ...  
WO/2010/036708A1
An actuator controller with a power supply that steps down a high voltage for use by remote auxiliary loads in an aircraft is provided. A high voltage power bus running through the aircraft may use high gage or smaller diameter wiring, r...  
WO/2010/010251A3
Assembly of actuators (1) and of a system for supplying electrical power, comprising an input unit (4) linking the actuators to a three-phase alternating electric current network (2) and to a control system (3), the input unit comprising...  
WO/2009/153011A3
An intersecting element (10) for connecting a first section of an aircraft supply system, which section is provided on an aircraft interior equipment component (12), to a second section of the aircraft supply system comprises a support s...  
WO/2010/010251A2
Assembly of actuators (1) and of a system for supplying electrical power, comprising an input unit (4) linking the actuators to a three-phase alternating electric current network (2) and to a control system (3), the input unit comprising...  
WO/2009/144345A1
The invention includes an auxiliary power unit (1) for supplying pneumatic and electrical power, the pneumatic power output of which is connected to a pipe (2) which traditionally includes bends (2), and elements for compensating (6) for...  
WO/2009/133218A1
The invention relates to a system comprising two independent pneumatic compressors (CAC) (2) with an electric power supply, connected to an independent CAC controller (5), and an auxiliary power unit (APU) (3) with dimensions such as to ...  
WO/2009/132846A2
The invention relates to an aircraft which comprises: a fuselage having a fuselage part (1), a power supply device (E), and at least two receiving devices (A) on the fuselage part (1) for fastening the power supply device (E). The invent...  
WO/2009/054926A3
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...  

Matches 201 - 250 out of 864