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Patent Searching and Data


Matches 301 - 350 out of 1,019

Document Document Title
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/2007/110494A1
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/2007/107731A3
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/2007/107732A1
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/2007/097772A3
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/2007/095935A2
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/2007/095935A3
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/2007/097772A2
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/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/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/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/2007/015695A2
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/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/2007/003755A1
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 ...  
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/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/2006/130454A2
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...  
WO2006058774A3
A supply system (100) for the energy supply in an aircraft comprising an engine (101) for propelling an aircraft, a fuel cell (102) for supplying an aircraft with electric energy, a first fuel reservoir (103) for supplying the engine (10...  
WO/2006/108125A2
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/2006/107741A3
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/2006/107741A2
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/2006/092478A1
The invention relates to a probe for measuring the thickness of frost accretion on a surface. According to the invention, the probe comprises a plurality of measuring stages (E1 to En) which are stacked at least substantially orthogonall...  
WO/2006/093480A1
An ice management system is configured for an aircraft having at least one rotor, each rotor having a plurality of blades. The system has an electrical power supply adapted to be carried by the aircraft remote from the rotor, and at leas...  
WO/2006/085054A1
An electrothermal heater mat for anti-icing or de-icing of a helicopter rotor blade or other aerodynamic surface comprises a substrate, such as a flexible polyimide sheet 6, bearing tracks 7A-7E of a material of selected electrical resis...  
WO/2006/063990A1
Disclosed is a rotor blade for a wind power station, comprising a rotor blade nose. A deposition sensor device is disposed in the area of the rotor blade nose. Said deposition sensor device is provided with a transmitter for the wireless...  
WO/2006/058774A2
A supply system (100) for the energy supply in an aircraft comprising an engine (101) for propelling an aircraft, a fuel cell (102) for supplying an aircraft with electric energy, a first fuel reservoir (103) for supplying the engine (10...  
WO/2006/052283A1
A system and method for detecting debris on the surface of a member are provided, for example, for detecting ice or other debris on an other surface of an aircraft. The detection system includes a heating device in thermal communication ...  
WO2006002224A3
A pulse electrothermal de-icing ("PETD") system for detaching ice includes a power supply (22) for applying a high-power heating pulse to the interface between ice and an object such as a cold plate of an ice making system, an ice-contai...  
WO2004105440A3
The invention relates to a heating device comprising a layer containing electrically conductive plastic. Said layer containing electrically conductive plastic exhibits an adhesive characteristic at least in some sections of at least one ...  
WO/2006/027624A1
An aircraft wing coupling arrangement couples services to and/or from a wing component which is translationally extendible from the wing of an aircraft. A housing (1) is provided for mounting on the wing and includes a first coupling mem...  
WO/2006/002224A2
A pulse electrothermal de-icing (“PETD”) system for detaching ice includes a power supply (22) for applying a high-power heating pulse to the interface between ice and an object such as a cold plate of an ice making system, an ice-co...  
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/2005/120948A1
A sensor system (300) comprises a first sensor (301), a second sensor (302), and circuitry (900). The first sensor (301) collects non-frozen liquid with a first collection efficiency, but does not collect frozen liquid. The second sensor...  
WO/2005/113336A1
Aircraft component, in particular a wing (1) with perforations (3) for boundary layer suction. In the space (5) between the double-walled wing (1), partition walls form pressure channels (21) and suction channels (22) that are adjacent t...  
WO/2005/087589A1
A laminate consisting of alternating metal layers (1) and plastic adhesive layers (2) located between the metal layers (1) for the production of structural parts such as panels that can be used in aviation and/or aerospace is characteris...  
WO/2005/073084A1
An aircraft system for control of the application of power to a plurality of devices (390, 391, 400, 401)in the aircraft comprises a plurality of local control modules (35, 36). Each local control module (35, 36) controls the application...  
WO2005006271A3
An acoustic wave sensor (10) utilizes one or more acoustic waves trapped in an acoustic wave cavity (12) to detect the presence of one or more substances on a surface (17) of the acoustic wave cavity. To detect the presence of ice, a tra...  
WO/2005/030578A1
An aircraft arrangement for Mini or Micro UAV comprising a fore wing (14) and an aft wing (12) in tandem closed-coupled arrangement. The aft wing (12) has side panels (18) and control surfaces (19), and tapered planform with positive swe...  
WO2003105532A8
The present invention relates to an electrically heatable glazing panel comprising a substantially transparent, electrically conductive coating layer which is adapted to be electrically heatable and is divided into a plurality of zones. ...  
WO2003105533A8
The present invention relates to an electrically heatable glazing panel comprising a substantially transparent, electrically conductive coating layer which' is adapted to be electrically heatable and is divided into at least two zones, e...  
WO/2005/020175A1
Methods and systems for detecting icing or incipient icing conditions external to a vehicle (100) are disclosed. An apparatus in accordance with one embodiment of the invention includes a temperature sensor (120) configured to direct a f...  

Matches 301 - 350 out of 1,019