Login| Sign Up| Help| Contact|

Patent Searching and Data


Matches 251 - 300 out of 1,041

Document Document Title
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/2009/059076A3
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/2009/085843A2
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/2009/077690A2
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/2009/077688A2
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/2009/055125A3
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/2009/068918A1
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/2006/107741A3
A deicing system includes dual deice system components to provide a redundant deice system. Each redundant portion of the system generally includes a controller, an air data computer, an ice rate controller, and an ice rate probe. The co...  
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/2009/060137A2
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/2009/060446A2
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/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/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/2009/055125A2
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...  
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/2009/007569A3
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/2009/025578A1
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/2009/001104A3
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/2009/004184A3
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/2009/023424A2
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/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/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/2009/004184A2
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/2009/000244A1
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/2008/138135A1
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/2008/104714A3
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/2008/132376A1
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/2008/059168A3
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/2008/057064A3
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/2008/054345A3
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/2008/107922A1
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/2008/103513A1
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/2008/051673A3
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/2008/059169A3
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/2008/087861A1
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/2008/059168A2
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/2008/057064A2
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/2008/053088A1
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...  

Matches 251 - 300 out of 1,041