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Matches 651 - 700 out of 1,043

Document Document Title
JP2013505426A
Directions of narrowband irradiation for defrosting or 脱氷 from the surface are provided. This technique is applicable to defrosting of various types, such as defrosting of a windshield, defrosting of airplane wings, and defrosting fo...  
JP5134371B2  
JP2009508746A5  
JP5112335B2  
JP2012533477A
A bus bar system includes a non-conductive substrate having a major surface. At least one conductive bus bar is formed over at least a portion of the major surface. A conductive coating is formed over at least a portion of the bus bar an...  
JP2012532051A
A method and a system for an integrated エゼクタ valve assembly are provided. The 1st valve assembly constituted by integrated エゼクタ valve assembly so that a flow of fluid with comparatively lower pressure from the 1st inlet p...  
JP5083918B2  
JP2012229690A
To provide a flow device adapted to operate as a restrictor and provide a pressure relief capability in the event of an over-pressurization event within a fluid system containing the device.The flow device 50 includes an expandable orifi...  
JP2012526705A
The device which removes ice from a subject (for example, defrosting from the shell of the airplane under flight) contains the actuator assembly which makes a long and slender conductive loop. An actuator corresponds to operation of the ...  
JP2012525476A
A composite structure includes a matrix material and a carbon nanotube (CNT)-infused fiber material that includes a plurality of carbon nanotubes (CNTs) infused to a fiber material. The CNT-infused fiber material is disposed throughout a...  
JP2012166656A
To assure a field of vision from a cockpit in case of emergency.The aircraft includes a camera 21, a display device 31 disposed in the cockpit C of an aircraft body, a final control element 32 which is disposed in the cockpit and starts ...  
JP2012166683A
To surely prevent widow fogging even when a part of a de-fogging device fails.The de-fogging device includes a main de-fogging device and a spare de-fogging device 20. The spare de-fogging device 20 includes a gas tank 21 stored with pre...  
JP2012148716A
To provide an anti-icing apparatus which is simple in configuration and prevents the icing of an aircraft flying in an icing environment, a wing, the aircraft and an anti-icing method.The anti-icing apparatus outputs pressure waves towar...  
JP2012132006A
To provide an article having ice phobic surface, and to provide a method of making and using the article.The article includes: a silicone composition disposed on a surface of the article; and a grease applied to the silicone composition,...  
JP2012514552A
[Subject] A method for removing external freezing of an airplane of enabling quick and reliable freezing removal of an airplane before starting is developed, and it carries out as [be / apparatus which requires structure top expense, hig...  
JP2012513932A
A lamination windshield of a transparent body, for example, an airplane, supervises performance of one or more character of heating arrangement composition of a windshield, for example, and is provided with one or more sensors which gene...  
JP2012513934A
A 防氷 system (200) includes the component-parts surface (202) which has the compound structure containing a composite layer (214), At least one heating element (220) currently formed in an inside of a composite layer (214) is assisted...  
JP2012514289A
A heating system (1) including an energy supply mechanism (5). A base heating machine style of an electric heat type provided with an insulating layer is provided with a base heating layer (10) laid in this, and an electric connection me...  
JP4959320B2  
JP4951616B2  
JP2012512749A
A device for maintaining a cutting edge, e.g. a focused laser beam at a constant distance from a surface of the work piece as the cutting edge imposes a cut line in a coating on the surface of the work piece. The device includes a consta...  
JP4934783B2  
JP4907830B2  
JP2012507424A
In order that the system (10) for cooling the heat exchanger (12) in an airplane may supply engine ブリード air to a process air line (28), the first end has the process air line (28) connected to the engine (16) of an airplane. The ...  
JP2012062049A
To provide a propeller blade having ice-phobic coating which is a passive system capable of improving reliability and maintainability and furthermore reducing both the initial acquirement cost and the maintenance cost during procession.T...  
JP2012507675A
A valve system includes a conduit having a flow of fluid therethrough, and a butterfly valve assembly. The butterfly valve assembly includes a shaft extending obliquely within the conduit, a butterfly disk, and a first bearing assembly p...  
JP2012046151A
To provide an aircraft ice protection system capable of efficiently implementing ice protection and improving aircraft performance such as prevention of decrease in main thrust and improvement in fuel economy, and to provide an aircraft ...  
JP2012505984A
The present invention is a multiplex windowpane unit (100) provided with at least three substrates (10, 20, 30) held together by the frame structure (90), In the multiplex windowpane unit (100) by which at least two middle gas-charging l...  
JP2011183922A
To properly prevent generation of ice adhered to the outside of a wing leading edge part by effectively heating the wing leading edge part, in an anti-icing and deicing device at the wing leading edge part in an aircraft and a main wing ...  
JP2011524300A
The system has pipes (2-4) for conveying gas from a source (1) to a work place (5) i.e. gas outlet. A flow rate determining device (7) determines gas mass flow in the pipes. A pressure determining device (9) determines static pressure in...  
JP4728325B2
The pressure channels (21) and suction channels (22) are formed between inner wall (29) and perforated outer wall (28) of the wing (1) by partitions (2). The pressure channels (21) with lesser perforated area (B), is connected through a ...  
JP2011520058A
A front tip structure used with an aerospace plane of this application contains a main part which has the channel surface which appoints a front tip which suited so that it might face in the style of air during an operation, and the inne...  
JP2011519401A
A front tip structure used with an aerospace plane of this application is provided with the following. A main part which has the channel surface which appoints a front tip which suited so that it might face in the style of air during an ...  
JP2011111158A
To quickly detect the presence of supercooled water drops larger than a threshold diameter without depending on an exciting circuit and a measuring circuit.This aircraft (1) includes a fuselage (2) and a detecting device (10). The detect...  
JP2011516344A
The present invention relates to a defrosting system for airplanes which has at least one air delivery means for sending air to at least one heat source and a portion in which an airplane should be defrosted. As compared with a prior art...  
JP2011516344T
The present invention relates to the defrosting system for airplanes which has at least one air delivery means for sending air to at least one heat source and the portion in which an airplane should be defrosted. As compared with a prior...  
JP2011095264A
To provide a method for reducing de-icing heater error (DHE) in a total air temperature (TAT) probe.Using the method, a nominal DHE function is obtained for a particular type of TAT probe as a nominal DHE function derived from a pluralit...  
JP2011093521A
To provide a thermal icing condition detector to solve problems of a conventional dry thermal sensor.In an icing condition detection system, a circuit 122 provides an output representing impending icing conditions as a function of power ...  
JP2011514465A
It is an engine air intake flap (K) carried at the 1st end (E1) and the longitudinal direction (L) of an air intake flap on the inspiratory port of the engine of the airplane which has the 2nd end (E2) that left the 1st end (E1) and is a...  
JP2011511732A
In a fibre composite component for an aircraft or spacecraft which has electrically conductive fibres at least in portions, the fibres are coupled with an electrical energy source for charging with current to heat up the fibres and/or fo...  
JP2011510861A
They are wings and an engine connection object provided with wings (W) which have a wing (W1), and an engine (E) which has a 予混合 chamber (E1), a combustion chamber, and high temperature air space (E2), a) An engine 抽気 suction s...  
JP2011505291A
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...  
JP2011505289A
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...  
JP2011504844A
The present invention relates to an energy supply system which operates at least one air-conditioning system (26) of an airplane in at least one air line network and at least one electric line network, An air line network is connected to...  
JP4620002B2  
JP2011500445A
An ice coating prevention system and a method for raising heat transfer contain a substrate which has the thickness which separates an inner wall, an outer wall, and an inner wall and an outer wall. A metal layer vapor-deposited on an in...  
JP4597527B2  
JP2010535668A
The present invention relates to an erosion resistant construction comprising an element of an aircraft comprising an aircraft skin segment having an external surface, and a deicing mechanism associated with said aircraft skin segment ca...  
JP2010234989A
To provide a blade structure capable of suitably preventing icing in an environment where it is exposed to high speed supercooling water droplets.On the surface of the blades of an aircraft, the surface of a blade front edge predicted to...  
JP2010202185A
To easily remove a deicing mat, in a method of mounting the deicing mat (3) to a blade structure (1).Shield foil (2) is shaped so that an inner surface (5) of the shield foil (2) has a shape that complements an external surface (6) of th...  

Matches 651 - 700 out of 1,043