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Matches 151 - 200 out of 750

Document Document Title
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...  
WO/2012/072451A1
Fuel cell systems aboard means of transport can be used for generating energy and for producing water. In order to reduce the overall weight of the system, the fuel cell is controlled or regulated in dependence on a current fill level or...  
WO/2012/069453A3
Energy supply network for an aircraft or spacecraft (1), comprising at least one energy generating device (7-1 to 7-6) for generating electrical energy, comprising at least two energy control devices (10, 12), at least one of which is co...  
WO/2012/069348A1
An aircraft (10) is equipped with an emergency power system (38) in the event of a loss of the main energy source (36), said emergency power system having a rotational energy supplying device (58) and a generator (48) that provides elect...  
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/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/2012/025687A3
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/2012/012474A3
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/2011/146021A1
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/2011/142844A3
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/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/2011/113696A3
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/2011/097156A3
The disclosure relates to a maintenance unit for servicing aircraft during stand-still, comprising electrically powered service and/or maintenance equipment. There is a power input for connecting the unit to an electrical power supply op...  
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/2011/089196A1
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/2011/072366A1
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/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/2011/051210A1
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/2011/037855A3
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/2011/037850A2
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/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/2011/023678A3
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/2011/023678A2
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/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/2010/146291A3
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/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/2010/112645A1
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/2010/105744A4
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/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/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/2010/080234A3
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/2010/066440A3
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/2010/066440A2
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/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/2010/046520A2
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/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/2010/040837A3
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/2010/036708A1
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...  

Matches 151 - 200 out of 750