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JP5233037B2 |
A de-icer device for de-icing an air inlet of a gas turbine, such as a helicopter turbine engine. The de-icer device includes an essentially metallic enclosure for admitting air into the engine, the enclosure including a first opening fo...
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JP5227320B2 |
A device for detecting and eliminating a layer of ice formed on the surface of an aircraft structure or a liquid that has infiltrated inside of a structure and/or into the material of the structure. The device includes at least one pair ...
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JP5224607B2 |
The invention relates to acoustic lining for an aircraft, which can cover a leading edge, such as an air inlet in the nacelle of a propulsion unit, said lining comprising: (i) from the inside outwards, a reflective layer (28), at least o...
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JP2013124096A |
To provide a seal assembly for sealing an aperture in a fixed leading edge for storing a strut of a translating cable device of an electric deicing system so as not to cause aerodynamic drag and undesirable flow disturbances, when the sl...
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JP5205383B2 |
Systems and methods for detecting ice particle accumulation is disclosed herein. In one exemplary implementation, a method for detecting ice is described in which a parameter within an interior volume of a heated conduit is measured. The...
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JP5192035B2 |
The invention relates to a coating for acoustic treatment at the surface of an aircraft, in particular at the leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer (28), at lea...
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JP5134371B2 |
An engine (101) propels the aircraft. A fuel cell (102) supplies electric energy to the aircraft. A kerosene reservoir (103) supplies the engine with engine fuel. A hydrogen reservoir (104) supplies the fuel cell with fuel cell fuel. The...
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JP5112335B2 |
According to the invention, on at least one of the faces (1E, 1I) of said leading edge (1), forward of the partition (3), an action is exerted on the fluid flow (EF) so as to cause the latter to switch from the laminar state (EFL) to the...
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JP5083918B2 |
The covering has a honeycomb type cellular structure (30) with a set of hexagonal shaped ducts emerging from a level of imaginary surfaces (34, 36). The structure has cuts or orifices (38) arranged at the level of lateral walls of one du...
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JP2012166656A |
To assure a field of vision from a cockpit in case of emergency.The aircraft includes a camera 21, a display device 31 disposed in the cockpit C of an aircraft body, a final control element 32 which is disposed in the cockpit and starts ...
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JP2012166683A |
To surely prevent widow fogging even when a part of a de-fogging device fails.The de-fogging device includes a main de-fogging device and a spare de-fogging device 20. The spare de-fogging device 20 includes a gas tank 21 stored with pre...
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JP2012148716A |
To provide an anti-icing apparatus which is simple in configuration and prevents the icing of an aircraft flying in an icing environment, a wing, the aircraft and an anti-icing method.The anti-icing apparatus outputs pressure waves towar...
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JP2012514552A |
In a method for exterior de-icing of an aircraft before takeoff, a region of the aircraft to be de-iced has hot air applied thereto and is heated, the air exiting a de-icing nozzle that can be disposed in the vicinity of the region to be...
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JP2012513934A |
An anti-icing system includes a component surface having a composite structure including a composite layer, and at least one heating element formed within the composite layer, wherein the heating element is configured to provide a transf...
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JP2012514289A |
A heating system (1) that includes an energy supply mechanism (5). The electric heating type base heating mechanism provided with an insulating layer includes a base heating layer (10) mounted therein and an electric connection mechanism...
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JP4959320B2 |
To provide a freeze preventing and removing device capable of easily and efficiently removing freeze on the surface of an object. A surface side electrode 4 in the shape of a concentric circle is formed on the surface of a glass layer fo...
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JP4951616B2 |
A dual primary deicing system for a rotary-wing aircraft, according to an exemplary aspect of the present disclosure includes, among other things, an electrothermal heating element system; and a controller in communication with said elec...
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JP2012512749A |
A device for maintaining a cutting edge, e.g. a focused laser beam at a constant distance from a surface of the work piece as the cutting edge imposes a cut line in a coating on the surface of the work piece. The device includes a consta...
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JP4934783B2 |
The device has an injector (12) for injecting pressurized hot air to a leading edge. A pressurized air intake (13) is mounted on a primary air generator. A transversal pipe (14) is connected to the air intake, and longitudinal pipes (9, ...
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JP4907830B2 |
A sensor for measuring physical parameters of a fluid, the sensor comprising an air intake fitted on a streamlined body, and a duct formed in said streamlined body to enable the fluid to flow and communicating with said air intake, the s...
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JP2012507424A |
A system for cooling a heat exchanger on board an aircraft includes an engine bleed air line connected to an engine of the aircraft and adapted to supply engine bleed air to the heat exchanger. The system further includes a process air l...
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JP2012507675A |
A valve system includes a conduit having a flow of fluid therethrough, and a butterfly valve assembly. The butterfly valve assembly includes a shaft extending obliquely within the conduit, a butterfly disk, and a first bearing assembly p...
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JP2011183922A |
To properly prevent generation of ice adhered to the outside of a wing leading edge part by effectively heating the wing leading edge part, in an anti-icing and deicing device at the wing leading edge part in an aircraft and a main wing ...
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JP4728325B2 |
The pressure channels (21) and suction channels (22) are formed between inner wall (29) and perforated outer wall (28) of the wing (1) by partitions (2). The pressure channels (21) with lesser perforated area (B), is connected through a ...
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JP2011516344A |
The invention pertains to a de-icing system for an aircraft with at least one heat source and at least one air delivery means for delivering air into regions of the aircraft to be de-iced. In comparison with the prior art, the invention ...
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JP2011516344T |
The present invention relates to the defrosting system for airplanes which has at least one air delivery means for sending air to at least one heat source and the portion in which an airplane should be defrosted. As compared with a prior...
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JP2011095264A |
To provide a method for reducing de-icing heater error (DHE) in a total air temperature (TAT) probe.Using the method, a nominal DHE function is obtained for a particular type of TAT probe as a nominal DHE function derived from a pluralit...
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JP2011093521A |
To provide a thermal icing condition detector to solve problems of a conventional dry thermal sensor.In an icing condition detection system, a circuit 122 provides an output representing impending icing conditions as a function of power ...
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JP2011514465A |
An engine inlet flap for mounting on the housing of an air inlet or air inlet duct of an engine of an aircraft, having a first end and a second end arranged in opposition thereto at a distance therefrom in the longitudinal direction of t...
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JP2011511732A |
In a fiber composite component for an aircraft or spacecraft which has electrically conductive fibers at least in portions, the fibers are coupled with an electrical energy source for charging with current to heat up the fibers and/or fo...
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JP2011510861A |
A wing-engine combination includes: a wing with a main wing and an engine with a premixing chamber, a combustion chamber and a hot-air space, which includes: an engine bleed-air duct, which extends along the wingspan direction and along ...
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JP2011504844A |
An energy supply system for operating at least one air conditioning system of an aircraft, comprises at least one air line network and at least one electric line network. The air line network is connected to the air conditioning system a...
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JP4620002B2 |
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JP2011500445A |
An icing protection system and method for enhancing heat transfer includes a substrate having an inner wall, an outer wall and a thickness separating the inner wall and the outer wall. A metallic layer deposited on the inner wall of the ...
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JP4597527B2 |
A windshield deicer has a windshield with a substantially transparent heating element that generates heat in response to applied power in a magnitude sufficient to melt an interfacial layer of ice on the windshield; and a controller for ...
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JP2010234989A |
To provide a blade structure capable of suitably preventing icing in an environment where it is exposed to high speed supercooling water droplets.On the surface of the blades of an aircraft, the surface of a blade front edge predicted to...
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JP4546537B2 |
An inverter system includes inverting circuitry for inverting an input DC signal into a square wave or quasi-square wave AC signal across a resistance, and a controller for causing the inverting circuitry to invert the input DC signal in...
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JP4510634B2 |
Methods and systems for providing secondary power to aircraft systems. In one embodiment, an aircraft system architecture for providing power to an environmental control system includes an electric generator operably coupled to a jet eng...
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JP2010520410A |
An air intake duct of an aircraft engine or other component is provided with a thermal anti-icing system. The front of the air intake duct comprises a toroidal outer skin (16) which forms, with a toroidal internal bulkhead (18), a toroid...
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JP4477497B2 |
The invention relates to a method and an apparatus for determining the risk of ice deposition due to precipitation. According to the invention the measurements of precipitation known so far are combined with measurements of the actual am...
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JP2010510120A |
An aircraft leading edge, such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, includes a coating (26) for the acoustic treatment that includes—from the outside to the inside—an acoustically resistive poro...
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JP4422907B2 |
Aircraft probe assemblies integrally include a total airstream temperature sensor. Preferred embodiments include at least one pressure sensing port and a temperature sensing port which are in fluid communication with a pressure sensing c...
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JP4424617B2 |
Methods and systems for detecting icing or incipient icing conditions external to a vehicle (100) are disclosed. An apparatus in accordance with one embodiment of the invention includes a temperature sensor (120) configured to direct a f...
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JP2010502518A |
A temperature monitoring arrangement for an electro-thermal ice protection system is provided for a slat of an aircraft wing, incorporating heater mats of composite material, wherein, in order to avoid or at least substantially reduce so...
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JP2009298198A |
To energy-savingly achieve ice prevention/removal of a structure body arranged in relative air streams.The ice prevention/removal device is provided with the structure body (wing body) 11; a nano-pin surface part 12 formed over a predete...
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JP2009543729A |
A heated leading edge component for an aircraft and a method of manufacture thereof. The leading edge component includes an outer skin, a supporting rib for the outer skin, and a cavity located substantially in-between the outer skin and...
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JP2009255925A |
To provide a system and a method for thermally changing the interface between ice and an object.A system includes a power source configured to be capable of generating a certain amount of power. The amount of power is great enough to mel...
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JP2009214873A |
To provide an anti-icing/de-icing system and a method using ultrasonic waves for an external surface of a structure likely to be iced, such as an aircraft wing or engine nacelle, and such a structure incorporating this system.The system ...
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JP4283583B2 |
There is described an electric connecting unit (2) for a helicopter (1), having a stator (15) connected rigidly to a fixed part (11) of the helicopter and fitted with first electric contact means (16); and a movable member (17) rotated a...
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JP2009096324A |
To simplify an air-bleeding system and reduce a load of an engine.This invention relates to an airplane air-bleeding system in which engine bleeding air is adjusted in its temperature and its pressure and supplied to an air-conditioning ...
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