Aircraft surface anti-icing and/or anti-misting system, method of control over said system and aircraft with said system |
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IPC classes for russian patent Aircraft surface anti-icing and/or anti-misting system, method of control over said system and aircraft with said system (RU 2406656):
 Electrothermal de-icing system, for example, for the blades of a helicopter / 2226481
The invention relates to aviation, in particular anti-icing systems for aircraft, and can be used to remove and prevent the formation of ice, for example, the rotor blades main and tail rotor
 System and method for producing electrical anti-icing coatings / 2218291
The invention relates to anti-icing systems for aircraft
 Thermal anti-icing system of the rotating element / 2093426
The invention relates to the field of aircraft electrical equipment and can be used in de-icing system with electric heating rotating parts of the aircraft, for example, Coca and the propeller blades of an airplane or helicopter blades, windmills and wind turbines
 Aircraft surface anti-icing and/or anti-misting system, method of control over said system and aircraft with said system / 2406656
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.
 Aircraft engine nacelle anti-icing system with resistive layer / 2411161
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.
 Section of gondola air intake edge with electric ice protection and acoustic absorption zone / 2422331
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.
 Article from composite material controlled by temperature and humidity and method of its production / 2432260
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.
 Method and device for control of power supplied to equipment to prevent ice formation or snow/ice removal from structural member / 2433938
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.
 Turbojet engine nacelle air intake downstream element and turbojet engine nacelle with said element / 2445237
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.
 Aircraft sound absorbing coating including anti-icing system exploiting joule effect / 2445238
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.
 Aircraft power supply circuit for electrical hardware including anti-icing circuit / 2450955
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.
 Device to detect and remove ice or fluid layer / 2453475
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.
 Device for ice removal from gas turbine air intake / 2481480
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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FIELD: transport. SUBSTANCE: 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. EFFECT: optimised aircraft anti-icing and anti-misting. 17 cl, 2 dwg
The object of the present invention is a system de-icing and/or condensation on the surface of the aircraft, such as the window of the cockpit of the aircraft, and how to control this system. The object of the invention is also an aircraft equipped with such a system. Protection against icing and fogging surfaces of the aircraft, usually carried out by means of heating elements, such as resistors. In the known technical solutions the power of the heating elements is performed by means of the relevant system, sometimes referred to as a transmitter of heat (or WHC-English Window Heat Computer"), which, in addition to the logic control operation, contains a switch, switchable thus, in order to apply for heating elements of electric energy corresponding to the intensity of the heat. Thus, according to this concept, the corresponding system constantly receives power from the main electrical system of the aircraft and sends electrical energy to the heating elements in a variable quantity, depending on the temperature measured by sensors placed at the level intended for surface treatment. In addition, the system will which replaces the function of the control current, which it sends to the heating elements, and for the correct operation of the sensors. Classical solution provides that the various elements of this system were inside the same complex, usually near the cabins, which affects the size and weight and, in addition, requires that this complex contained all the circuits necessary for its operation (in particular, the power switch and the logical circuit including the transmitter). To avoid these problems and to optimize the concept of the system de-icing and/or fogging to use the existing functionality of other systems of the aircraft, the present invention proposes a system de-icing and/or condensation on the surface of the aircraft, characterized in that it contains: - temperature sensor located close to the said surface and configured to generate temperature information; - the transmitter is configured to generate control information on the basis of the temperature information, and transmitting control information in a computer network of the aircraft; system electric power made with the possibility of receiving control information over a computer network and contains off the switch, made with the ability to switch depending on the control information; - heating element located near said surface and receiving electric power through the above mentioned switch. Thus, the switching of a switch included in the electrical power, that is, as a rule, at the level of the Central electrical system of the aircraft, which allows you to refuse the commutated switch, usually located in the cab. In this application, the phrase "near the surface" should be understood: on the surface or on the high from her distance, which provides a physical interaction with the surface. Power-supply system contains, for example, a microprocessor, connected to a computer network. Thus, the microprocessor can receive control information and to control switching of the switch depending on the control information. In practice, the microprocessor may control switching of the switch with a signal, the cyclic ratio of which depends on the control information. According to a variant implementation, the transmitter receives temperature information from the sensor through the analog connection. A computer network is, for example, on-Board network type Ethernet. According to the capabilities of the applications, the calculator included in the control module heating, connected to a computer network. In this case, the control module heating may contain controls for the sensor, configured to alarm in a computer network in the event of a malfunction of the sensor. This module, which can be located anywhere on the aircraft (for example, in the side compartment of the aircraft, controls, thus, the logic control system instead of the commonly used classical system. In addition, the power-supply system can include a means of measuring the strength of the current passing through the switch, is arranged to control the opening operation of the breaker and/or generating an alarm signal in a computer network in case of exceeding a certain threshold. Thus, the shut-off functions and monitor the correct operation of integrated power supply system. Control system alarms connected to a computer network, in these two cases can output the signal to the display unit in the cockpit in case of receipt of an alarm signal. The said surface is, for example, the window of the cockpit of the aircraft. In accordance with the present invention a method for managing system fight about what lagenarium and/or condensation on the surface of the aircraft, characterized in that it contains the following steps: - definition of the management information on the basis of temperature information obtained from the temperature sensor located close to the said surface; transmission of control information in a computer network of the aircraft; - obtaining management information system electric power; depending on the control information, switch switch, through which electrical power to the heating element, located close to the said surface. Typically, the switch is part of a system of electric power and is, therefore, at the level of Central electrical system of the aircraft. The method may include the preliminary step of transmitting the sensor temperature information through the analog connection. When the said switch is controlled by a microprocessor system electric power, the method may also include the step of accepting the mentioned microprocessor control information. The object of the present invention is also an aircraft which use these inventions. Other distinguishing features of the present invention are evident from the following description given with reference to the accompanying drawings, is which: Figure 1 - key elements of the system de-icing in accordance with the present invention. Figure 2 - block diagram of the operation of the system shown in figure 1, in the normal mode. Figure 1 schematically shows the crew cabin 2 aircraft, which has a lot of window 4 through which the crew monitors the surrounding space. Each of these glasses are connected to the heating elements 6 (of which figure 1 shows only one). When these heating elements 6 are activated (i.e. receive electric power), they provide protection of the 4 Windows from icing (and therefore from fogging). In practice, the heating elements 6 made for example in the form of resistor circuits, which are made in the glass 4 at the level of its surface; these resistor circuit can be located, for example, between different layers of glass window panes. What follows is a description of only one of the heating element 6, as the other heating elements operate in the same manner. The electric circuit shown in figure 1 as a single conductor, although in practice there is also a reverse transmission circuit current (for example, through a lot). The heating element 6 is fed from a source 10 voltage through a power switch 8, which allows you to adjust the electrical power supplied to the th on the heating element 6, what will be described below. Source 10 voltage is performed, for example, by combining the inverter and rectifier. We are talking about AC voltage (typically 115 VAC or 200 VAC)received from the power generation means of the aircraft. Power switch 8 includes an electrically operated switch 12 and the microprocessor 14, which contains a PWM output to control the switch 12. The signal values at the output PWM controls the closing and opening operation of the switch 12. The switch 12 is connected between the source 10 voltage and the heating element 6. The microprocessor 14 also contains the contact 15 for measuring the current I flowing through the switch 12. The microprocessor 14 is connected via the bus to other electronic modules, described below in connection with the computer network 18 (often called side network, for example, type "Ethernet", such as AFDX network, described for example in patent application FR 2832011). Power switch 8 and the source 10 voltage, which form a system of electric power to the heating element 6, preferably located at the level of Central electrical system of the aircraft. Numerous functional modules (often called CPIOM from the English "Core Process Input Output Module) connected to the network 18. Among these functional module is shown in figure 1 only, involved in the system de-icing in accordance with the present invention, namely the module 20 heat control window and the module 22 controls alarm. Module 20 heat control window can interact with the microprocessor 14 of the power switch 8 and the module 22 controls alarm signals through a computer network 18. In addition, the module 20 heat control window receives temperature information TRT in analog form from the sensor 5 located at the window level 4 (usually inside box 4), which contains the heating element 6. (As in the case of item 6, to simplify the drawing shows only one sensor 5). Module 20 heat control window performs the following functions, which will be described below: - monitoring the temperature information TRT coming from the sensor 5 and simultaneously monitoring the reliability of these data, i.e. during normal operation of the sensor 5); - management of the heating element 6 in dependence on the measured temperature, that is, in practice, the determination of control information intended for the circuit of the power switch 8, on the basis of the temperature information TPT coming from the sensor 5; - the transmission of an alarm signal to the control system 22 alarms in the learn the detection of a fault in the work, for example, at the level of the sensor 5. It should be noted that to generate the control information, if necessary, you can use other parameters, such as the speed of the aircraft or the mode (manual or automatic) power control, and this task is made easier due to the fact that the module 20 is in the on-Board network. As mentioned above, the control system 22 alarms can interact with other functional modules (in particular, the module 20 heat control window) and with the power switch 8 via a computer network 18. Module 22 controls alarming signals may also control the necessary actions of one of the other blocks in the case of the receipt of the alarm signal. He may, for example, display the symbol denoting the corresponding alarm signal, the device 24 display located in the cab 2. Functional modules 20, 22 may be located anywhere in the aircraft, because they interact with other elements via the network 18. Preferably the functional modules 20, 22 are grouped in the appropriate place in the plane, called a side compartment. Next, with reference to Figure 2 follows the description of the operation of the system de-icing in normal mode. In the module 20 to control the heating of Windows do you rate acorna information TRT from the sensor 5 (step E102), and on the basis of these data it defines, in particular, CMD, designed for power switch 8 (step E104). Control information CMD receive, for example, depending on the temperature information TRT and from the setpoint temperature (recorded, for example, in the memory module 20 with possibility of adjustment) using lookup tables stored in memory module 20. Management data CMD show, for example, the number of rated power of the heating element, which must be released to reach a given temperature. In a variant, we can talk about cyclic ratio at which the switch should alternately be opened or locked. Control information CMD transmitted by the module 20 to control the heating of Windows in a computer network 18 (step E) in digital form. Control information CMD can, therefore, act in the microprocessor 14 of the power switch 8 (step E). On the basis of the control information CMD microprocessor 14 determines the cyclic ratio command signal PWM that is intended for transmission to the control contact switch 12 (step E110), to the level of the heating element 6 to obtain the release of the required heating power (i.e. the corresponding command data CMD). In normal mode maintains deistvie the above-described various elements allows you to adjust the temperature at the window level 4 and therefore, to provide protection from freezing (as well as from sweating). What follows is a description of several examples of outputs in normal mode. As indicated above, the microprocessor 14 includes a contact 15, which allows to control the current I passing through the switch 12. If the microprocessor 14 determines that the current I is too strong (for example, due to malfunction of the switch 12 or the result of excessive voltage source 10 voltage), he gives a command for opening the switch 12. Thus, the power switch 8 has the function of the chopper. In the case of anomaly detection in the measurement of the current passing through the switch 12, the microprocessor 14 may also send the appropriate alarm signal to the module 22 control alarm, the crew learns about anomalies with the help of the device 24 to display. Another type of alarm signal in the above-described system de-icing refers to a malfunction of the sensor 5. As mentioned above, the system 20 to control the heating of Windows takes not only the temperature information TRT, but also defines the information about the correct operation by monitoring the sensor 5. In the case of anomaly detection in sensor 5 module 20 heat control window, the last parade the appropriate alarm signal to a computer network 18 and 22 control alarms. Thus, this system can warn the crew of a failure of the sensor 5 by the output of the corresponding symbol on the display device 24. In case of detection of a malfunction of the sensor 5 module 20 heat control window can also give the command data CMD value that ensures reliable operation regardless of the actual temperature (i.e. presumably not certain) on the window 4, namely, for example, control information CMD, which disables heating or, in a variant, the heating power of the heating element 6 is determined depending on the other parameters measured on Board the aircraft. The above example represents a possible embodiment of the invention, which does not limit its scope. 1. The system de-icing and/or condensation on the surface (4) of the aircraft, characterized in that it contains 2. The system according to claim 1, characterized in that the system (8) electric power contains a microprocessor (14)connected to the computer network (18). 3. The system according to claim 2, characterized in that the microprocessor (14) is configured to receive control information (CMD) and switching control of the switch (12) in dependence on control information (CMD). 4. The system according to claim 3, characterized in that the microprocessor (14) controls the switching of the switch (12) using the signal, the cyclic ratio of which depends on the management data (CMD). 5. The system according to claim 1, characterized in that the transmitter (20) receives the temperature information (TRT) from the sensor (5) via an analog connection. 6. The system according to claim 1, characterized in that the transmitter is included in the module (20) to control the heating, connected to a computer network (18). 7. The system according to claim 6, characterized in that the module (20) control agrevo which contains controls for the sensor (5), made with the possibility of alarm in a computer network (18) in the event of a malfunction in the sensor (5). 8. The system according to claim 1, characterized in that the system (8) electric power includes means (15) to measure current (I)flowing through the switch (12)which has a capability of generating an alarm signal in a computer network (18) in case of exceeding a certain threshold. 9. The system according to claim 7 or 8, characterized in that the system (22) control alarm connected to a computer network (18) and configured to output the signal to the device (24) display booths in the case of obtaining mentioned alarm. 10. The system according to claim 1, characterized in that the system (8) electric power includes means (15) to measure current (I)flowing through the switch (12), arranged to control the opening operation switch (12) in case of exceeding a certain threshold. 11. The system according to claim 1 or 3, characterized in that the computer network (18) is the on-Board network type Ethernet. 12. The system according to claim 1, characterized in that the said surface is a window (4) cabin crew of the aircraft. 13. The way the control system de-icing and/or condensation on the surface (4) of the aircraft, otlichalis the same time, it contains the following stages: 14. The method according to item 13, characterized in that it includes a step (E) transmission sensor (5) temperature information (TRT) through the analog connection. 15. The method according to item 13 or 14, characterized in that, as mentioned switching is controlled by a microprocessor (14) system (8) electric power, the method includes a step (E) receiving the said microprocessor (14) control information (CMD). 16. The aircraft, characterized in that it contains a system according to claim 1. 17. The aircraft, characterized in that it contains means is arranged to apply the method according to item 13.
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