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Matches 251 - 300 out of 1,022

Document Document Title
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...  
WO/2009/050454A1
A leading edge component (30) for an aircraft. The component includes at least one supporting rib (40); a skin of the leading edge; and an ice-protection system comprising a thermoelectric heater mat (10) located between the rib and the ...  
WO/2009/025578A1
The invention relates to mechanical engineering and can be used in the aircraft industry for ground testing of aerospace engineering objects exposed to icing under natural operating conditions. The inventive method consists in simulating...  
WO/2009/023424A2
The present disclosure provides a tape comprising: a) a single layer comprising a crosslinked polymer, selected from the group consisting of crosslinked polyurethane, crosslinked polyurea, and crosslinked mixed polyurethane/polyurea poly...  
WO/2009/023424A3
The present disclosure provides a tape comprising: a) a single layer comprising a crosslinked polymer, selected from the group consisting of crosslinked polyurethane, crosslinked polyurea, and crosslinked mixed polyurethane/polyurea poly...  
WO/2009/019696A3
An aircraft deicing system including at least one motor operative to drive at least one eccentric mass in rotational motion and at least one displacer coupled to at least one location on at least one aircraft surface and coupled to the a...  
WO/2009/010431A1
The invention relates to an aircraft wing comprising a fixed wing central body and a leading edge mobile flap shutter (16) intended to be rotated with respect to the fixed body in a circular path that lies within a sphere of centre (C). ...  
WO/2009/007569A2
The invention relates to a defogging or de-icing system for an optical instrument including a protection housing (1). According to the invention, the system includes: a porthole (2) covered on at least one face thereof with a heat conduc...  
WO/2009/007569A3
The invention relates to a defogging or de-icing system for an optical instrument including a protection housing (1). According to the invention, the system includes: a porthole (2) covered on at least one face thereof with a heat conduc...  
WO/2009/004184A3
The invention concerns a procedure for collecting information concerning a mobile aerodynamic aircraft surface (10), comprising the stage of collecting information by means of an adapted sensor placed directly on the aerodynamic surface....  
WO/2009/004184A2
The invention concerns a procedure for collecting information concerning a mobile aerodynamic aircraft surface (10), comprising the stage of collecting information by means of an adapted sensor placed directly on the aerodynamic surface....  
WO/2009/001104A2
There is disclosed an ice protection system for a structure (1100), the ice protection system comprising: a plurality of independently controllable heater elements (1108, 1110, 1112) arranged on the structure; and a control system, opera...  
WO/2009/001104A3
There is disclosed an ice protection system for a structure (1100), the ice protection system comprising: a plurality of independently controllable heater elements (1108, 1110, 1112) arranged on the structure; and a control system, opera...  
WO/2009/000244A1
The invention relates to a detection device for detecting ice deposits on gas turbine components (12). The detection device comprises a film (32) and a conductor track arrangement (18, 20) for forming at least one sensor (16) that is emb...  
WO/2008/148543A1
The invention relates to a structural component (10) for an aircraft, said component having an outer section (14-1, 14-2) with an outer surface (12) that is at risk of ice accumulation thereon (e.g. airfoil system of an airplane). The ai...  
WO/2008/139117A1
According to the invention, the method comprises exposing a surface (3) sensitive to relative wind and monitoring the thermal flow variations between the surface (3) and the aerodynamic flow, said variations resulting from that of the fo...  
WO/2008/138846A3
A method and an apparatus for initiating a run-up procedure for a jet engine to avoid engine icing, the method comprising the following steps of providing at least one surface element that is made of a material suitable for ice in atmosp...  
WO/2008/138135A1
The invention provides systems to optimize the heat being transferred from a gaseous heat carrier to a contaminated surface. The invention also provides Retraction/Deployment System to facilitate the transportation of delivery heads.  
WO/2008/132376A1
The invention relates to a device (50) for de-icing the air intake (249 of a gas turbine (10), such as a helicopter turboshaft. The invention is characterised in that the device includes an essentially metal housing (52) for the air inta...  
WO/2008/131098A1
Apparatus, methods, and systems for ice detection using a reference probe (101) and a collection probe (102) to detect ice formation on an aircraft.  
WO/2008/107922A1
An article (1) of composite material includes a plurality of plies of material (10) consoliĀ¬ dated through the application of pressure and heating, in which each material ply is made by a resin matrix reinforced with fibre material. The...  
WO/2008/107678A1
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 toroi...  
WO/2008/104714A3
The invention relates to a coating for the acoustic treatment of the surface of an aircraft, especially at the level of a leading edge such as the air intake of an aircraft nacelle, said coating including an acoustically resistive layer,...  
WO/2008/103513A1
A system for detecting ice of a particular thickness includes a structure from which ice forms, and an ice detection assembly movably secured to the structure. The ice detection assembly includes a transducer operatively connected to a s...  
WO/2008/087861A1
A leading edge structure of aircraft comprises a body part (11) constituting the leading edge part (1) of the aircraft and a surface part (12) which is formed on the outer surface of the body part (11) and on which a large number of pins...  
WO/2008/077101A1
A light source (401) is disposed in an aircraft (400) along with a light-to-electricity converter (403) and an optical pathway (404) that transports light (402) from that light source to the light-to-electricity converter. An energy stor...  
WO/2008/062148A1
A leading edge structure (30) for an aircraft and a method of making the same. The leading edge structure includes an outer skin (60), a laminated electric heater (62) attached to an inner surface of the outer skin, and a matrix of holes...  
WO/2008/059169A3
The subject of the invention is an aircraft leading edge such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, comprising a covering (26) for acoustic treatment comprising, from the outside inwards, an acoustic...  
WO/2008/059168A2
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...  
WO/2008/059169A2
The subject of the invention is an aircraft leading edge such as, for example, an air intake (22) of a nacelle (14) of a propulsion unit, comprising a covering (26) for acoustic treatment comprising, from the outside inwards, an acoustic...  
WO/2008/059168A3
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...  
WO/2008/057064A2
Conducting- fiber deicing systems and methods are disclosed. In one embodiment, an assembly includes a surface (128) subject to an accumulation of ice, the surface (128) at least partially including a heating portion (152) having a layer...  
WO/2008/057064A3
Conducting- fiber deicing systems and methods are disclosed. In one embodiment, an assembly includes a surface (128) subject to an accumulation of ice, the surface (128) at least partially including a heating portion (152) having a layer...  
WO/2008/053088A1
The invention relates to an nacelle member (1) comprising at least one mobile cowling (2) pivotally or slidably mounted in an essentially longitudinal direction of the nacelle, capable of displacement between an expanded position and a c...  
WO/2008/054345A3
An apparatus for an airplane or other equipment is provided. The apparatus may comprise a multitude of connected arms (52', 54) which are adapted to rotate relative to one another. One end of the apparatus may be connected to a fixed win...  
WO/2008/054345A2
An apparatus for an airplane or other equipment is provided. The apparatus may comprise a multitude of connected arms (52', 54) which are adapted to rotate relative to one another. One end of the apparatus may be connected to a fixed win...  
WO/2008/053087A1
The invention relates to a nacelle including an air intake upstream from the jet engine (1), a medium section surrounding the fan of the jet engine (1), and a downstream section. The nacelle further includes at least one pair of mobile c...  
WO/2008/051673A3
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...  
WO/2008/051673A2
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...  
WO/2008/017606A1
A sensor for sweat or other aqueous discharge onto skin comprises a plastic optical fibre comprising a core and cladding, said core being in intimate contact at a first end with a light emitter and at a second end with a light detector, ...  
WO/2008/015362A1
The invention concerns a rear frame of an air intake of a nacelle of an aircraft, characterized in that it is partly made of fiber-reinforced geopolymer resin-based composite material and comprises at least one part (56) that surrounds a...  
WO/2008/015356A1
The invention concerns a device for detecting and eliminating a layer of ice formed on the surface of an aircraft structure (6) or a liquid that has infiltrated inside of a structure and/or into the material of the structure. According t...  
WO/2008/009921A1
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...  
WO2007095935B1
An aerodynamic profile (10) for aircraft and wind energy plants comprises an aerodynamically formed structure (11), in which, for example, a phased ultrasound emitter arrangement (12) is arranged, which emits ultrasound waves in particul...  
WO/2007/138450A8
The invention relates to a method and a system for detecting the risk of icing on aerodynamic surfaces lapped by a fluid flow (F), in particular on load-bearing surfaces of fluid machines, of the type comprising a temperature sensor (20)...  
WO/2007/138450A1
The invention relates to a method and a system for detecting the risk of icing on aerodynamic surfaces lapped by a fluid flow (F), in particular on load-bearing surfaces of fluid machines, of the type comprising a temperature sensor (20)...  
WO/2007/135383A1
A layered heating system for heating a leading edge component of an aircraft . The system includes a removable heating layer (20). The system also includes a layer (30) for removably adhering the heating layer to the leading edge compone...  
WO/2007/136260A1
An aerodynamic profile (1) having walls built up from fibre reinforced polymer material. Near the outer surface of the wall electrical conductive elements (7) are provided such as metallic wires. More particular, stainless steel wires ar...  
WO/2007/134866A1
Control device for a tensioning and lifting mechanism of an upper part of a vehicle tarpaulin, with at least one air hose which has an inlet line (1) for connecting a main pressure regulator (2) to the compressed air system of a vehicle,...  
WO2007097772A9
A region of an airfoil to be protected from accreted ice is heated to reduce the strength of t  

Matches 251 - 300 out of 1,022