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Electric impulse de-icing device Electric impulse de-icing device may be used for ice removal from metal sheet surfaces, for example, from wings covering of air planes. The claimed device comprises a number of inductors placed closed to de-iced metal surface. The inductors are coupled to outputs of the respective modules, which inputs are connected through a circuit breaker to the supply mains. Each of the modules comprises a charger, a storage capacitor, a monitoring key, a protective diode and control pulse generator. The charger input is coupled to the module output while its output is coupled to the storage capacitor. Output of the storage capacitor through the monitoring key is coupled to the module output. The protective diode is connected in parallel to the module. Besides, the claimed device is equipped with an adjustable control pulse delay unit and low-energy supply unit. The module input is coupled to the supply unit input while feeding inputs of the generator and adjustable control pulse delay unit are coupled to the module output. The generator and adjustable control pulse delay unit are coupled in series. Input of the monitoring key is coupled to output of adjustable control pulse delay unit. |
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Antiicing device, in particular for aircraft nacelle Set of inventions relates to aircraft equipment. antiicing device(1) for aircraft nacelle contains electrical tapes (5) each one of which is made of main conductor (7) oriented along tape (5) which includes straightline elements (13) and curved elements (17. The tapes (5) include spirals (15) formed by combination of several curved elements (17). Adjacent tapes (5) are built in pairs and are powered from different sources. Air intake edge of aircraft includes antiicing device (1). |
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Power supply circuit for aircraft deicing system Aircraft power supply circuit includes on-board power distribution network (17) for electric devices (5b) located in or near the aircraft engine, and power supply generator (27) integrated in the aircraft engine to supply AC power to deicing system (5a). Power supply generator is connected to electromechanical drive of thrust reverser (5c) via rectifier to supply DC power to the mentioned drive. |
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Electric anti-icing device and corresponding monitoring system Invention relates to aircraft engineering, namely, to an anti-icing device for one of the elements of a turbojet engine gondola. The device contains an electro-thermal anti-icing device connected to a power source (3) and thus forming a group (1) of electro-thermal anti-icing devices. The group of electro-thermal anti-icing devices includes one or more subgroups of electro-thermal anti-icing devices each one of which includes in its turn one or more electro-thermal anti-icing devices of a group where separate subgroups of electro-thermal anti-icing devices have different values of ohmic resistance. |
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Method of arranging anti-icing system at nacelle panel Invention relates to aircraft engineering, particularly, to anti-icing system at nacelle panel 22. Proposed method comprises the following stages: a) positioning device 35 arranged at outer skin 24 is used to position screen composed of resistive elements around opening or openings. b) appropriate means is used to apply the screen of resistive elements to area defined at step (a) to form anti-icing system. c) surface coat is applied on produced anti-icing system. |
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Method of control over electric deicing system Invention relates to aircraft engineering, particularly, to control over at least one resistive heating element 1 incorporated with turbojet nacelle deicing system. It differs from know designs in that it includes the steps whereat parameters of external flight conditions are received from aircraft central control unit 6 and definition of heat model corresponding to flight conditions. Depending upon selected heat model required electric power 4 is fed to said resistive heating element. |
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Method of nacelle deicing element fabrication Invention relates to aircraft engineering, particularly, to aircraft nacelle deicing element. Proposed method comprises the following stages: (a) matrix of heating resistors is produced in substrate by photolithography; (b) composite sheet 50, 52 is placed on matrix produced at step (a); (c)inner shell 12 is applied on thus made deicing assy 13. |
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Method of making acoustic panel for nacelle air intake Invention relates to aircraft engineering, particularly, to production of acoustic panel for aircraft intake edge and to air intake edge with such panel and to gas turbine nacelle. Method of making acoustic panel 12 for edge 2 at nacelle air intake 1 comprises production of deicing assy 14 including gauze of conducting elements made by photolithography. Note here that said deicing assy 14 is secured to structure 13 with cellular core. |
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Turbojet nacelle air intake edge Invention relates to aircraft engineering, particularly, to air intake deicing systems. Turbojet nacelle air intake edge 4a is equipped with electric deicing device 11 arranged at its inner surface including at least one panel comprising cellular structure 13 of electrically conducting material and electric connectors 21, 22 connected to said structure. Cellular structure cells are arranged perpendicular to panel plane. Said cellular structure is composed of some parallel strips 16, two of them converge and diverge in turns to make the cells hereupon. Strips 16 may be glued or welded together Said panel comprises first and second connectors 21, 22. Note here that first ends of every strip. Said panel is equipped with electric insulators 23 covering the cellular structure edges. Device 11 can remove ice and kill ice at a time. |
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Device for ice removal from gas turbine air intake Device (50) for ice removal from air intake (24) of gas turbine (10) includes metal cover (52) for air intake (24) of the gas turbine. The cover includes the first air inlet opening (54) to cover (24), which is equipped with the first metal grid (56). The cover includes the second opening (58) intended for air direction to compressor stage (20) of the gas turbine. Device includes means (62, 64) for generation to the cover of electromagnetic waves having the frequency allowing to melt the ice. The helicopter turbine engine is characterised by use of the air intake ice removal device. |
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Device to detect and remove ice or fluid layer Proposed device comprises, at least, two subnets 2a, 2b of conducting elements. Every said subnet comprises, at least, one line of elements 3. Subnets are arranged so that finger joint between first subnet conducting element 3 and second subnet conducting elements 3 make network of capacitance pickups. Said conducting elements double as heating elements designed to eliminate icing. Conducting elements are buried in insulation material 4. Every subnet of conducting elements is integrated in flexible backing 5, 5a, 5b. The complex proper makes flexible coating. Aircraft comprises above described device connected to crew cab instrumentation panel via switch to display operating parameters and to control said device. |
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Aircraft power supply circuit for electrical hardware including anti-icing circuit Set of invention relates to aircraft electric power supply circuit. Proposed circuit comprises power distribution circuit 16 and electric hardware supply circuit 5b, and electric power generator 27 incorporates with aircraft engine to supply anti-icing circuit 5a. Electric hardware comprises nacelle consuming components 5b connected DC voltage distribution with bus 35 connected with voltage converter circuit 34 supplied by distribution circuit 17. Anti-icing circuit 5a comprises, at least, one resistor 61 to dissipate electricity sent back to DC voltage distribution circuit 35 by, at least, some of nacelle consuming components. Aircraft comprises above described power supply circuit. |
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Aircraft sound absorbing coating including anti-icing system exploiting joule effect Invention relates to aircraft engineering, particularly, to power plant air intake and aircraft sound-absorbing coating. Said coating may close air intake front edge and comprises, on one side, reflecting layer extending from inside to outside, cellular structure and sound-absorbing structure. On the other side, coating incorporates ice processing system made up of heating layer containing open zones to transmit acoustic waves. Sound-isolation structure comprises structural layer with holes. Note that heating layer is located under said structural layer. |
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Turbojet engine nacelle air intake downstream element and turbojet engine nacelle with said element Invention relates to turbojet engine nacelle air intake edge attached to downstream section of said air intake that comprises anti-acing electrical hearing element, and to appropriate downstream section and turbojet engine nacelle. Downstream element 4b of air intake 4 of nacelle 1 allows air intake edge 4a to attached thereto. Edge 4a comprises anti-icing electrical hearing element 14. Edge 4a consists of identical sections 7 butt-jointed together along perimeter of air intake 4. Said element 14 is furnished with connector assembly 15 secured in front web 18 of downstream element 4b. Said element 4b comprises power supply connector assembly 19 to interact with connector assembly 15 of edge 4a. |
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Group of inventions refers to control devices of supplied electric power in order to prevent ice formation or to remover snow/ice from structural member surface. In the method the supply of power us controlled by means of controller which is operated on the basis of values of physical parameters which are measured by means of transmitters located on structural member and on the basis of preceding measurement data referring to snow or ice conditions. Input data is temperature of structural member, amount of snow/ice on structural member, air temperature, wind velocity, precipitation, speed of structural member and the corresponding vibrations. The above input data is compared to the stored data of preceded measurements by means of controller. After comparison the controller calculates by using the defined algorithm the required power, as well as required values of current load and frequency. Frequency influences the temperature change time constant of structural member surface. Then, controller supplies start or stop signals to power supply equipment. After that, controller modifies the stored data with new data of values of parameters, which are the consequence of current snow/ice state on structural member in compliance with pre-set sequence. |
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Article from composite material controlled by temperature and humidity and method of its production Invention relates to method of controlling humidity absorption in article mounted in aircraft. Proposed article comprises multiple layers of material from resin matrix reinforced fibrous material to be hardened by pressure and heat. Heating electric resistor and temperature metre connected with control means are arranged between said layers. |
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Section of gondola air intake edge with electric ice protection and acoustic absorption zone Inventions relate to aircraft engineering, more specifically to the section of gondola air intake edge, edge of air intake for turbojet engine gondola and turbojet engine gondola. Section (7) of turbojet engine gondola (1) air intake (4) edge (4a) contains outside shell (12) and inside shell (13) as well as electric heating element (14) located between the inside shell and the outside shell and made with possibility to be connected to power supply facilities (15, 16). Herewith, the electric heating element passes through acoustic absorption zone having holes (11) which go through this section and contact with acoustic absorption device (30) attached to inside shell. In this structure, the air intake edge can be made of one or more such sections. |
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Aircraft engine nacelle anti-icing system with resistive layer Invention relates to aircraft engineering, particularly, to aircraft engine nacelle anti-icing system that comprises air intake 2 equipped with bead 3. Air intake tubular part 4 with acoustic isolation panel 5 is arranged behind said bead. Besides, proposed system comprises anti-icing appliances (6, 6a, 6b, 6c, 6d) made up of the grid of resistive heating elements immersed in electro-insulating material. Note here that said anti-icing appliances are made up of a layer comprising resistive elements arranged in depth of air intake bead. Proposed system forms a part of bead wall that overlaps bead part 3a external with respect to air intake. |
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Set of invention relates to aircraft surface anti-icing and/or anti-misting system, method of control over said system and aircraft with said system. Temperature transducer is arranged nearby protected surface to generate temperature data. There is a computer to generate control data proceeding from said temperature data and transfer it into aircraft computer network. Electric power supply system is arranged in aircraft central electric system to receive control data via computer network and incorporates switch operated depending upon control data. Heating element is located nearby protected surface and receives power supply via said switch. In control effected by said system, control data is determined received from temperature transducer. Control data is transmitted into aircraft computer network and received by electric power supply system. Depending upon control data, switched in switched to feed power supply to said heating element. |
Another patent 2550911.