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Matches 201 - 250 out of 1,019

Document Document Title
WO/2010/086524A1
The invention relates to a de-icing device for an element of a nacelle of a turbojet engine, including at least one heating resistant mat connected to at least one electrical power source (3) and thus defining an assembly (1) of resistan...  
WO/2010/074942A1
An anti-icing system (200) includes a component surface (202) having a composite structure including a composite layer (214), aid at least one heating element (220) formed within the composite layer (214), wherein the heating element (22...  
WO/2010/070273A1
In a first aspect the invention relates to a sensor system (10) for determining a proximity to icing conditions of an environment. The system includes a sensor having a sensor surface (12) for exposure to the environment, an electrically...  
WO/2010/055215A1
The present invention relates to a method for commanding and controlling at least one resistive heating element (1) belonging to an aircraft turbojet engine nacelle deicing set, characterized in that it involves the steps aimed at: obtai...  
WO/2010/026305A1
The invention relates to a method for making an acoustic panel (12) for an air intake lip (2) of a nacelle (1) that includes the steps of obtaining a perforated de-icing assembly (14) including at least one array of conducting members ob...  
WO/2010/026304A1
The invention relates to a method for making a nacelle element (2) that includes the steps of: (A) forming an array of heating resistors on a substrate using a photolithographic method; (B) applying a web (50, 52) of composite materials ...  
WO/2010/015758A1
The invention relates to a method for making a deicing system on a panel (22) of a nacelle comprising an outer skin (24) having at least one hole and an inner skin (26), characterized in that it comprises the following steps: A. a grid o...  
WO/2010/006946A1
The invention relates to a device (20) and a method for avoiding ice-buildup on a surface area (22) of an aircraft (10) and/or for de-icing the surface area (22). In the process, a laser (1) is used, said laser being adapted to emit onto...  
WO/2010/004262A2
Composite structural components are disclosed that include electrically conducting fibres providing signal power paths to electrical components disposed on or adjacent the material. The signal paths may therefore be embedded in the struc...  
WO/2009/153033A2
The invention relates to an aircraft conduit monitoring system comprising a conduit that conducts gas from a source to a point of application. A flow sensing device and a pressure sensing device are provided within the conduit. At least ...  
WO/2009/150326A1
A structural element of an aircraft comprises a hollow part. An indicator (40) provides a visual indication (for example by moving) if ice forms in a given region of the hollow part.  
WO/2009/142793A3
A leading edge structure for use in an aerospace vehicle includes a body (38) having a flowpath surface (48) which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented i...  
WO/2009/142793A2
A leading edge structure for use in an aerospace vehicle includes a body (38) having a flowpath surface (48) which defines a leading edge adapted to face an air flow during operation, and an opposed inner surface. The body is segmented i...  
WO/2009/138833A3
Coupling for inducing high temperature drops on parts of an aircraft comprising an edge portion (2) subjected to high temperature and a bearing structure (3) having limited capacity to resist against high temperatures. Such coupling comp...  
WO/2009/134526A1
A leading edge (39) structure for use in an aerospace vehicle includes a body- having a flowpath surface (40) which defines a leading edge adapted to face an air flow during operation; and a metallic icephobic plating (42) comprising nic...  
WO/2009/130400A1
The invention relates to a de-icing and/or anti-icing system for the leading edge of an aircraft wing or for the lip (1) of the air intake of an aircraft engine, characterised in that it includes a plurality of infrared emitting members ...  
WO/2009/127652A3
The invention relates to a de-icing system for an aircraft, comprising at least one heat source (28) and at least one air discharging means (23) for discharging air in areas of the aircraft to be de-iced. The invention is characterized i...  
WO/2009/127652A2
The invention relates to a de-icing system for an aircraft, comprising at least one heat source (28) and at least one air discharging means (23) for discharging air in areas of the aircraft to be de-iced. The invention is characterized i...  
WO/2009/122066A3
The invention relates to a lip that includes, on the inner surface thereof, an electric de-icing device (11) comprising at least one panel including a cellular structure (13), made of electrically conductive material, and an electrical c...  
WO/2009/121806A2
The present invention relates to a device for erosion protection and icing protection of a flow element (1) for an airplane. The device comprises a film element (3) and a drive apparatus (4). The film element (3) is configured for form-f...  
WO/2009/122066A2
The invention relates to a lip that includes, on the inner surface thereof, an electric de-icing device (11) comprising at least one panel including a cellular structure (13), made of electrically conductive material, and an electrical c...  
WO/2009/121806A3
The present invention relates to a device for erosion protection and icing protection of a flow element (1) for an airplane. The device comprises a film element (3) and a drive apparatus (4). The film element (3) is configured for form-f...  
WO/2009/112743A1
The invention relates to an air supply device that includes: a duct (20) for supplying pressurised air, connected to the engine, and including radial openings (29) and an upstream wall (28); a duct (21) for distributing air in the de-ici...  
WO/2009/112695A1
The invention relates to an air intake structure capable of being mounted upstream of a central structure of a nacelle for an aircraft engine, the said air intake structure comprising: - an external wall incorporating a lip, - an upstrea...  
WO/2009/097668A2
Aircraft air scoop icing protection systems and methods include an air duct having air inlet and outlet openings and a fairing which covers the air duct and defines an interior fairing space in which at least a forward portion of the air...  
WO/2009/098044A1
Engine inlet flap (K) for mounting on the housing of an air inlet or air inlet duct of an engine of an aircraft, having a first end (E1) and a second end (E2) arranged in opposition thereto at a distance therefrom in the longitudinal dir...  
WO/2009/097668A3
Aircraft air scoop icing protection systems and methods include an air duct having air inlet and outlet openings and a fairing which covers the air duct and defines an interior fairing space in which at least a forward portion of the air...  
WO/2009/095335A2
Disclosed is a fiber composite part (1) for an aircraft or spacecraft, comprising electrically conductive fibers (6) in at least some sections. The fibers (6) are coupled to an electric power source to apply electricity in order to heat ...  
WO/2009/095335A4
Disclosed is a fiber composite part (1) for an aircraft or spacecraft, comprising electrically conductive fibers (6) in at least some sections. The fibers (6) are coupled to an electric power source to apply electricity in order to heat ...  
WO/2009/096838A1
The invention relates to a de-icer (20), comprising a bracket (52) arranged on a structural member and a de-icer module (22) mounted on the bracket (52). The de-icer module (22) is adjustable arranged on the bracket (52), so that the pos...  
WO/2009/095335A3
Disclosed is a fiber composite part (1) for an aircraft or spacecraft, comprising electrically conductive fibers (6) in at least some sections. The fibers (6) are coupled to an electric power source to apply electricity in order to heat ...  
WO/2009/085843A3
An aircraft component (200) includes a first segment (110) having a first leading edge surface that extends to a first end (222) of the first segment. The aircraft component also includes a second segment (112) having a second leading ed...  
WO/2009/085843A2
An aircraft component (200) includes a first segment (110) having a first leading edge surface that extends to a first end (222) of the first segment. The aircraft component also includes a second segment (112) having a second leading ed...  
WO/2009/081020A1
The invention relates to an acoustic processing structure provided at a leading edge on which flows an aerodynamic stream, in particular at the air inlet of an aircraft nacelle, wherein said acoustic processing structure includes, from t...  
WO/2009/077688A3
The invention relates to an aircraft nacelle that comprises a discharge means (50) for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (54, 56), and at which...  
WO/2009/077690A2
The invention relates to an aircraft nacelle that comprises a duct (32), a peripheral wall (34), a front lip (36) connecting said duct (32) and said peripheral wall (34) and defining an air inlet, as well as an ice treatment system for t...  
WO/2009/077666A2
The invention relates to a lip assembly (1) for the air inlet of a turbojet engine nacelle, that comprises an inner surface (9), an outer surface (11) and de-icing means, wherein the de-icing means includes an anti-ice coating (13) cover...  
WO/2009/077690A3
The invention relates to an aircraft nacelle that comprises a duct (32), a peripheral wall (34), a front lip (36) connecting said duct (32) and said peripheral wall (34) and defining an air inlet, as well as an ice treatment system for t...  
WO/2009/077688A2
The invention relates to an aircraft nacelle that comprises a discharge means (50) for establishing a communication between the inside of the nacelle and the outside thereof, and a junction area between two members (54, 56), and at which...  
WO/2009/077666A3
The invention relates to a lip assembly (1) for the air inlet of a turbojet engine nacelle, that comprises an inner surface (9), an outer surface (11) and de-icing means, wherein the de-icing means includes an anti-ice coating (13) cover...  
WO/2009/068918A1
A temperature monitoring arrangement for an electro-thermal ice protection system is provided for a slat (2) of an aircraft wing, incorporating heater mats 121, 122, 123, 124 of composite material, wherein, in order to avoid or at least ...  
WO/2009/060446A3
A method of preventing the formation of ice layers on solid surfaces of various geometries and materials exposed to humid and super-cool environment is provided. The area to be protected is covered by fibrous or porous structures impregn...  
WO/2009/060137A2
The invention relates to an air intake structure that can be mounted upstream of a nacelle middle structure for an aircraft engine, and that particularly includes: an outer wall (7) including a lip (9) and that can be mounted relative to...  
WO/2009/060137A3
The invention relates to an air intake structure that can be mounted upstream of a nacelle middle structure for an aircraft engine, and that particularly includes: an outer wall (7) including a lip (9) and that can be mounted relative to...  
WO/2009/060446A2
A method of preventing the formation of ice layers on solid surfaces of various geometries and materials exposed to humid and super-cool environment is provided. The area to be protected is covered by fibrous or porous structures impregn...  
WO/2009/059076A2
Systems and methods for pulse electrothermal and heat-storage ice detachment. A pulse electrothermal ice detachment apparatus includes one or more coolant tubes, and optionally, fins in thermal contact with the coolant tubes. The tubes a...  
WO/2009/059076A3
Systems and methods for pulse electrothermal and heat-storage ice detachment. A pulse electrothermal ice detachment apparatus includes one or more coolant tubes, and optionally, fins in thermal contact with the coolant tubes. The tubes a...  
WO/2009/055125A3
An icing protection system and method for enhancing heat transfer includes a substrate (52) having an inner wall (42), an outer wall (44) and a thickness separating the inner wall and the outer wall. A metallic layer (54) deposited on th...  
WO/2009/055125A2
An icing protection system and method for enhancing heat transfer includes a substrate (52) having an inner wall (42), an outer wall (44) and a thickness separating the inner wall and the outer wall. A metallic layer (54) deposited on th...  
WO/2009/050460A1
An aircraft leading edge ice protection system. The system includes: a thermoelectric heater mat (10) attachable to a leading edge component of an aircraft, the heater mat comprising: an electrically resistive heater element (12, 22) emb...  

Matches 201 - 250 out of 1,019