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WO/2012/001302A2 |
Apparatus comprising a fixed part, a rotary support able to be rotated with respect to said fixed part, at least one item of electrical equipment (23) carried by said rotary support, and a power supply device able to provide electrical e...
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WO/2011/161377A2 |
The invention relates to a method of detecting a fault with the means for de-icing a probe for measuring a physical parameter on an aircraft engine, comprising the successive steps consisting in: - measuring a first value (T1) of the phy...
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WO/2011/127996A1 |
The present invention describes a blade (100) for a wind turbine. The blade (100) comprises a heating mat (101) for generating heat by resistive heating, wherein the heating mat (101) is mounted to the blade (100). The heating mat (101) ...
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WO/2011/127997A1 |
The present invention relates to a blade (100) for a wind turbine. The blade (100) comprises a heating mat (101) for generating heat, wherein the heating mat (101) is mounted at an outer surface of the blade (100). The heating mat (101) ...
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WO/2011/110659A1 |
The invention relates to a device for determining the operational state of an electro-expulsive deicing system (1) including a current pulse generator (3) and an electro-expulsive mat (2), a sensor (4) connected between the current pulse...
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WO/2011/111405A1 |
Disclosed are a deicing device for the leading edge of the wing of an aircraft and an aircraft main wing, which are configured by being provided with: a warm air path (46) which is formed along the inside of the curved leading edge (41) ...
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WO/2011/096851A1 |
The invention regards a de-icing/anti-icing system comprising at least two conductive structures (3', 3") embedded in an article (2), which includes an outer surface (5) being designed as an aerodynamic surface, at least one of the condu...
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WO/2011/092483A1 |
An electrothermal heater mat (3) is provided for an ice protection system for an aircraft (1) or the like. The heater mat (3) is a laminated heater mat and comprises dielectric layers (50-58), a heater element (501) and a temperature sen...
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WO/2011/092482A1 |
An electrothermal heater mat (3) is provided for an ice protection system for an aircraft (1) or the like. The heater mat (3) is a laminated heater mat and comprises dielectric layers (50-58), a heater element (501) and a conductive grou...
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WO/2011/092481A1 |
An electrothermal heater (2) for an ice protection system for an aircraft (1) or the like is provided with improved protection against lightning strikes. The heater (2) comprises a laminated heater mat (3) formed from dielectric layers (...
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WO/2011/087412A1 |
The invention regards a de-icing/anti-icing system comprising at least two conductive structures (3', 3") embedded in an article (2), which includes an outer surface (5) being designed as an aerodynamic surface, at least one of the condu...
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WO/2011/087413A1 |
The present invention regards a structural article comprising an outer surface (5), which serves as an aerodynamic surface when the structural article (1) is subjected for an air stream, the structural article (1 ) comprises a resin matr...
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WO/2011/073565A2 |
The subject of the invention is an aircraft nacelle air intake comprising a duct extending around the circumference of said air intake and means (24) for the localized injection of hot air into said duct to make the hot air circulate in ...
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WO/2011/073561A1 |
The invention relates to an air inlet of an aircraft nacelle including a pipe, extending over the circumference of said air inlet and defined in the back by a front frame, and a means for the localized injection of hot air into said pipe...
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WO/2011/064531A2 |
The present invention relates to an improved sensor arrangement, a system and method for determining the rate of ice formation and how close conditions are to those at which ice will form on a surface, and to an improved sensor arrangeme...
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WO/2011/035259A1 |
A way of using narrowband irradiation to de-ice or release ice from a surface is provided. The methodology can be applied to a range of different types of de-icing from windshield de-icing to aircraft wing de-icing to releasing ice from ...
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WO/2011/020964A1 |
The present invention relates to the use of a method for ion implantation into the surface of a material so as to modify the surface properties of said material in order to produce an anti-icing surface, as well as to a method using this...
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WO/2011/018695A1 |
A wind turbine having at least one air foil with a leading edge and a trailing edge and in which the air foil is rotatably mounted about an axis. A thermoelectric film is disposed over at least a portion of the leading edge of the air fo...
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WO/2011/008333A1 |
A heated guide vane for turbomachinery includes a guide vane having two major surfaces joined about their periphery by edges and an electric heater element, wherein the electric heater element is secured to at least one major surface of ...
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WO/2011/000081A1 |
An aircraft anti-icing composition is provided comprising a freezing point depressant and a thickener comprising nanocrystalline cellulose. A thickening composition is also provided comprising nanocrystalline cellulose. Also taught is th...
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WO/2011/002481A2 |
An apparatus for removing ice from an object (e.g., in-flight ice removal from the skin of an aircraft) includes an actuator assembly that forms an elongated electrically conductive loop. The actuator is mounted in a position enabling it...
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WO/2010/141228A1 |
A system for detecting ice of a particular thickness includes an ice-forming housing, and an ice detection assembly pivotally secured to the ice-forming housing. The ice detection assembly includes a deflection arm, and one of a sensing ...
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WO/2010/133602A2 |
The invention relates to a method for protecting a part of a surface of an aircraft against soiling with insect residues and/or against icing, comprising the following steps: a) coating the part of the surface to be protected with a coat...
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WO/2010/128239A2 |
The invention relates to a deicing device for propfan-type aircraft propeller blades, whereby the propulsion unit (1) comprises a turbine engine (8) rotating at least one rotor (3a) having a plurality of blades (4a) disposed around a rin...
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WO/2010/128299A1 |
A heating system for heating at least a portion of a leading edge (114) of an aircraft wing (112). The system comprising a first portion (5) of a heat pipe (4) positioned between an end of an aircraft wing support rib (6) and a portion o...
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WO/2010/128240A2 |
The invention relates to a deicing device for propfan-type aircraft propeller blades, whereby the propulsion unit (1) comprises a turbine engine (8) rotating at least one rotor (3a) having a plurality of blades (4a) disposed around a rin...
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WO/2010/112453A1 |
The present invention relates to a rotating inlet cowl (30) for a turbine engine, having a rotational axis (34) and the front end of which is eccentric to said rotational axis (34). Further, a front cone (32) of the cowl is truncated by ...
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WO/2010/103212A1 |
The invention relates to a de-icing device (1) in particular for an aircraft nacelle comprising at least two electric bands (5) each made from at least one main conductor (7) oriented substantially along the length of said band (5), char...
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WO/2010/103104A1 |
An engine and pod assembly for an aircraft including a pod (4) receiving an engine (1) having an air intake (2) wherein a rotating nose cone (3) extends as well as a device for limiting the formation of ice on the nose cone, with the dev...
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WO/2010/089496A1 |
The invention relates to an acoustic processing panel mounted at the air intake of an aircraft nacelle, said panel including at least one acoustically resistive structure (30) and a reflective layer (32), between which are provided, in a...
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WO/2010/089497A1 |
The invention relates to a method for making an acoustic processing panel, comprising an acoustically resistive porous layer (12), at least one cellular structure (14), a reflective structure (16) with openings, and a drainage plate (22)...
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WO/2010/086560A2 |
The invention relates to an aircraft nacelle including a duct (32), a peripheral wall (34), a lip (36) and a front frame (38) connecting the peripheral wall (34) and the duct (32) and defining a gap (50) with the lip (36) in which hot ai...
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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...
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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...
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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...
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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...
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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...
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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 ...
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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...
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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...
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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...
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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 ...
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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.
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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...
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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...
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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 ...
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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...
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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...
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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...
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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...
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