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Matches 301 - 350 out of 1,065

Document Document Title
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...  
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/2008/051673A2
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/2007/072027A3
A method of heating an aircraft fuselage comprises the step of supplying heat energy to air occupying an interior space enclosed by an aircraft fuselage shell structure so as to drive moisture from air in a region disposed immediately ad...  
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...  
WO/2007/097772A3
A region of an airfoil to be protected from accreted ice is heated to reduce the strength of the bond between the ice and the airfoil, and is mechanically deformed to shed the accreted ice after the bond has been sufficiently weakened. H...  
WO/2007/129907A3
In order to remove snow or ice from an exposed constructional element (1) by means of electric current in a heat emission equipment (3), the supply of power is controlled by way of a controller (13) operating based on physical parameter ...  
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/2007/107731A3
There is disclosed an electrical system for an aircraft comprising: at least one generator (302); a power control system (304) for distributing power from the generator to electrical subsystems (306, 308) in the aircraft; and an ice prot...  
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  
WO/2007/129907A2
In order to remove snow or ice from an exposed constructional element (1) by means of electric current in a heat emission equipment (3), the supply of power is controlled by way of a controller (13) operating based on physical parameter ...  
WO/2007/122307A1
The present invention relates to a lip (4a) of an air inlet (4) of a turbojet pod (1) intended to be fastened to an air inlet downstream structure (4b) and including at least one electric heating element for defrosting, said electric hea...  
WO/2007/118263A1
The invention relates to a method for removing icing from an aircraft surface by heating parts of the iced aircraft surface, the ice being detached from the outer surface (7) by a film of water and a simultaneous thermal and/or mechanica...  
WO/2007/095935A3
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/2007/110494A1
The present invention relates to a structure (7) for a lip (4a) of an air inlet (4) of a turbojet pod (1) comprising an outer skin (12), designed to be oriented towards the outside of the lip, and an inner skin (13), designed to be orien...  
WO/2007/110499A1
According to the invention, a sealed articulation device (27) is mounted on at least one (14) of the branches (14; 18, 9) of said hot-air circulation circuit in the form of a bracket so as to provide said bracket with capabilities of def...  
WO/2007/107713A1
A method of making a heater structure and a corresponding heater structure are disclosed. The method comprises providing a porous reinforcement material such as glass cloth, applying a metal to the porous reinforcement material such as b...  
WO/2007/107732A1
An ice protection system is disclosed for a structure having at least one surface to be protected from a range of icing conditions, the ice protection system comprising: at least one heater device (108, 110, 112), arranged in thermal con...  
WO/2007/107731A2
There is disclosed an electrical system for an aircraft comprising: at least one generator (302); a power control system (304) for distributing power from the generator to electrical subsystems (306, 308) in the aircraft; and an ice prot...  
WO/2007/095935A2
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/2007/097772A2
A region of an airfoil to be protected from accreted ice is heated to reduce the strength of the bond between the ice and the airfoil, and is mechanically deformed to shed the accreted ice after the bond has been sufficiently weakened. H...  
WO/2006/130454A3
A rotor blade of a helicopter is presented. In an embodiment, the rotor blade (100) includes a body (105) ; and a heating mat (301) arranged in the body (105) and configured to supply heat to said body. The heating mat (301) includes a f...  
WO/2007/080333A1
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...  
WO/2007/072027A2
A method of heating an aircraft fuselage comprises the step of supplying heat energy to air occupying an interior space enclosed by an aircraft fuselage shell structure so as to drive moisture from air in a region disposed immediately ad...  
WO/2006/136748A3
The invention concerns a deicing and anti-icing system for an aircraft engine pod, comprising an air intake (2) provided with a lip (3) followed by an air intake tubular part (4), equipped with a first sound attenuating panel (5), compri...  
WO/2004/110864A3
A rig for use in conjunction with a helicopter or other aircraft which allows the aircraft to be quickly converted to use as platform for rappeling. The rig is preferably constructed of stapping materials into relatively plannar main bod...  
WO/2007/034074A1
The invention concerns a system for deicing and/or defogging an aircraft surface (4) comprising: a temperature sensor (5) located proximate said surface (4) and adapted to generate a temperature information (TPT); a computer (20) adapted...  
WO/2007/015695A3
In an aircraft windshield (4) defogging/deicing system, a pair of transparent sheets (8) maintained in spaced facing relation by a transparent interlayer (14) have a resistive coating (20) positioned between the transparent sheets. An in...  
WO/2007/015695A2
In an aircraft windshield (4) defogging/deicing system, a pair of transparent sheets (8) maintained in spaced facing relation by a transparent interlayer (14) have a resistive coating (20) positioned between the transparent sheets. An in...  
WO/2006/001830A3
An ice protection system (19) for a structure (25) has at least one electro-thermal heating element (23) carried by the structure (25) and a controller (21) for selectively controlling the operation of each heating element (23). The cont...  
WO/2007/003755A1
The invention concerns a laminate comprising a conductive fabric web (2) consisting essentially of electrically conductive material fibers, said web is provided with a terminal (2) designed to be connected to an electric current source, ...  
WO/2006/136748A2
The invention concerns a deicing and anti-icing system for an aircraft engine pod, comprising an air intake (2) provided with a lip (3) followed by an air intake tubular part (4), equipped with a first sound attenuating panel (5), compri...  
WO2006108125A3
An. electrothermal deicing apparatus comprises: at least one heater conductor (12) formed into a predetermined pattern for application to a structure, each conductor of the pattern coated with at least one layer (14) of a material active...  
WO/2006/136680A1
The system for defrosting the leading edge sheath of an air intake hood for a turboengine comprises a hot pressure air supply duct (60) and a protective shell (90) which are longitudinally rigid and rigidly fixed to the partition (5) of ...  

Matches 301 - 350 out of 1,065