Electrothermal de-icing system, for example, for the blades of a helicopter |
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IPC classes for russian patent Electrothermal de-icing system, for example, for the blades of a helicopter (RU 2226481):
  
 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
System and method for producing electrical anti-icing coatings / 2218291
The invention relates to anti-icing systems for aircraft
System and method for producing electrical anti-icing coatings / 2218291
The invention relates to anti-icing systems for aircraft
 How to replace the elastic sealing rings in ball joints of pipeline anti-icing system for aircraft / 2211984
 The method of surface treatment of aircraft icing and mobile installation for its implementation / 2204494
The invention relates to vehicles adapted to spray
 A device for determining the intensity of icing / 2169105
The invention relates to equipment aircraft
 Mobile unit for de-icing of the external surfaces of the aircraft / 2159198
The invention relates to equipment for de-icing of the external surfaces of the aircraft on the ground
 The way deformation of the structure and its environment and device for its implementation / 2132292
The invention relates to the field of electro-education electrical energy into mechanical work and is intended for use with the excitation drums, acoustic, hydraulic and geophysical waves
 Device for determination of intensity of icing and thickness of ice / 2243923
Device includes first and second thermostabilizers, power difference separation unit, non-linear member, integrator and second indicator; first thermostabilizer is connected by its input to temperature sensor of working sensitive element and its output is connected to heater of working sensitive element; input of second thermostabilizer is connected to temperature sensor of compensating sensitive element and its output is connected to heat of compensating sensitive element.
 Mobile plant for de-icing of flying vehicles, industrial objects and structural objects / 2268200
Proposed mobile plant is made on base of automobile 1 with hoisting mechanism 2 for operator cabin equipped with remote control console 4, working fluid storage reservoir 5, pipe line with nozzle 7 connected with systems supplying it under pressure to surfaces to be treated, device for heating working fluid, detergent reservoir 10. Working fluid supply system includes pump connected with oil tank and with automobile engine through gearbox electrically connected with control console. Working fluid heating unit is made in form of flow-through device.
 Air intake for flying vehicle engine / 2279998
Proposed air intake for flying vehicle engine includes heated leading edge with skin, diaphragm and air supply branch pipe, outer skin of air intake and air inlet duct consisting of two parts. Front part of this duct is secured on outer skin and rear part is secured on engine flange. Front and rear parts of air inlet duct are interconnected by means of flexible coupling and are mounted at clearance forming circular slit. Located concentrically on front part of air inlet duct is envelope having longitudinal joint and its front end face is rigidly secured on Z-shaped profile mounted in duct. Vertical web of profile has holes smoothly distributed over perimeter. Rear end face of Z-shaped envelope is engageable by its lug with duct and its wall has holes smoothly distributed over perimeter.
 Method and device for detection of impairment of flying vehicle characteristics / 2302359
Central unit is connected with many information sources for detection of impairment of flying vehicle characteristics. Central unit is connected with warning units. Central unit includes computers for determination of present mass and present drag of flying vehicle and theoretical drag on basis of present mass. Central unit is also provided with device for use of at least first set of comparisons pertaining to drag and one comparison between preset drag and theoretical drag and devices for determination of impairment of flying vehicle characteristics by at least first set of comparisons.
 Device for determining rate of icing and thickness of ice deposit / 2307050
Invention relates to devices for measuring rate of icing and thickness of ice deposit on aircraft surfaces. Proposed device contains ice detector including working and compensating sensors and provided with heaters and temperature sensors. First thermostabilizer is connected by first input to temperature sensor of working sensor and by output, to heater of working sensor. Second thermostabilizer is connected by first input to temperature sensor of compensating sensor and by output, to heater of compensating sensor. Power difference discriminator is connected by first input to output of first thermostabilizer and by second input, to output of second thermostabilizer and by its output, to input of first nonlinear element whose output is connected to first indicator and to integrator, output of the latter being connected with second indicator. Moreover, device includes ambient air temperature meter and second nonlinear element. Output of ambient air temperature meter is connected to input of second nonlinear element whose output is connected to second inputs of first and second thermostabilizers.
 Device for supply of hot gas to flying vehicle movable slat or to stabilizer / 2316452
Proposed device is made in form of pipe line with inlet branch pipe (6) mounted on movable slat, outlet branch pipe (1) mounted on wing and elbow. Branch pipes and elbows are interconnected by means of bearing units. Bearing units include rotating bearings located in bodies; elbows are interconnected by means of bearing unit (5) provided with spherical bearing at slide fit over inner diameter; sealing rings of spherical bearing and packing washers of rotating bearing flanges are made from metal.
 Method and device for detection of icing / 2323131
Proposed method includes calculation of period of digitization frequency and delay time for compensation of initial phase shift, harmonic analysis of Fourier transformation, calculation of frequency and resonance Q-factor, detection of icing on basis of these data, calculation of ice thickness and rate of icing. Device proposed for realization of this method includes icing sensor with temperature sensor, transmitting converter, resonator, receiving converter and heating element, as well as processing unit with transceiver, signal processor, power amplifier, frequency synthesizer, amplifier with programmed gain factor and switch.
 System of protection of object surface from ice formation / 2329182
Invention refers to protection of object surfaces from ice formation and can be used on aircraft for ice formations removal. The system of protection contains inductors assembled under protected from ice formation surface of a coat; the said inductors are connected to impulse distributing units. These units are connected to a unit generating high voltage impulses; the latter is electrically tied with an output of a thickness indicator unit. The total thickness of the coat and a current conducting screen installed between the coat and the inductor must be not less, than a depth of penetration of electromagnetic field which is generated with an inductor coil. The current conducting screen with a diameter equal to a diameter of a working surface of the inductor is fixed rigidly to the coat via a flexible component placed between them; a diameter of the said component is equal to a diameter of the screen. The inductor is assembled against the screen with a gap of 0.1-0.2 mm.
 Icing indicator of helicopter propeller blades / 2335434
Indicator includes optical emitter mounted in the upper part of helicopter fuselage, which, via transmitting optical system, polariser, optically transparent heated emitter cap generates pulse emission at frequency of pulse oscillator connected to optical emitter. Pulse emission is modulated and synchronised using modulator and synchroniser which control pulse oscillator. Emission, reflecting from reflecting surface of propeller blade front edge, arrives on photoelectric detector input via optically transparent heated photoelectric detector cap. Polarisation plane of analyser is turned relative to polarising surface of polariser by the angle providing absence of emission passing through analyser when reflecting from clean surface of propeller blade. Input of signal processing unit is connected to output of photoelectric detector and output of signal processing unit is connected with input of icing indicator and input of anti-icing system control unit. The device allows to record with high accuracy the moments of icing process start and termination for helicopter lifting propeller blades.
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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. Electrothermal de-icing system contains teploelectrocental heaters, connected in series with the thyristor switches. Teploelectrocental heaters are mounted in pairs, connected by conductors in the end portion of the blade, with each subsequent pair of heaters covers the previous pair. The heaters have a variable resistance across the length of the blade. To monitor the health of the system installed current transformers, the windings of which are connected to operational amplifiers. Power supply to the heaters is carried out by the control unit in the sequence diagram with time delay between cycles, dependent on the outdoor temperature. The technical result is to reduce the weight and improve the reliability of the de-icing system. 6 C.p. f-crystals, 4 Il.
The invention relates to aviation, in particular anti-icing systems for aircraft, and can be ispolzovat.
Known anti-icing device for helicopter main rotor containing a heating resistance, powered from three-phase on-Board power supply via slip rings and contactors that are controlled by software device that switches the power circuits for the thyristors, and managing the software distributor is carried out through slip rings using a modulated signal (ed. St. USSR №454729. De-icing device for the rotor of a helicopter, MCI 64 D 15/12, BI, No. 47, 25.12.1974). A disadvantage of the known anti-icing device is no possibility of adjusting the heating time of the heating devices in accordance with their characteristics, which may lead to the formation of a barrier of ice.
Known anti-icing system of the aircraft, containing the alarm system, sensor icing temperature sensor with the sensor element and the corresponding converters, block the formation of teams with the dispenser, the output of which through the contactors connected heating elements heated surfaces, a threshold device limiting the length of the heating alameen inputs of the device simulation of the heating process are connected with the corresponding outputs of the distributor, the output of the simulation is connected to the input of lock issue commands dispenser through the block comparison, the other input of which is through a threshold device limiting the length of the heating elements associated with the Converter temperature sensor, and the control trigger is connected by one input to the inverter icing, the other to one of the outputs of the distributor and its output to the input schema matching, the other input of which is connected to one of the outputs of the distributor, and the output to one of the inputs of the distributor (ed. St. USSR №669638. Anti-icing system of the aircraft, MCI 64 D 15/12, BI No. 37, 07.10.1986). A disadvantage of the known anti-icing system is that in the scheme of switching power supply circuits of the heating elements are electromagnetic contactors, there is no control circuit power heaters. This leads to reduction of operational reliability, great weight system.
Known electric de-icing device containing three-phase collector and three-circuit of the switching elements through which electric heaters, combined in groups of three heating element in each is a software switch, each of the power circuits of the heating elements of the respective group split into two, with two phases of one of the split circuits connected to the heating elements in the bypass switching element, and in the third phase, each of the split circuits connected to the heating element through independent switching circuit (patent USSR No. 695546. Electric anti-icing device, MCI 64 D 15/12, BI No. 40, 30.10.1979). A disadvantage of the known anti-icing device is the design complexity, lack of control circuit power heaters, which reduces reliability.
Known electrothermal system cyclic actions for airframe components, which contains groups of heating elements, each group contains three elements, one of which has the power, twice each item separately. Elements of dual power connected with software switch through the switching elements and normally closed relay contacts connected to the additional control channel (patent RU №1633720. Electrothermal system cyclic actions for airframe components, MCI 64 D 15/12, IB No. 31, 10.11.1996). Neuslechtila anti-icing system of the plane cyclic actions. The system contains heating elements, three-phase contactors, transformers and control unit. The inclusion of the heating elements is controlled by the control unit on the signals taken from the control contacts of the corresponding contactor. When a short circuit of the heating element at the output of the current transformer of a signal, and when the cliff, hence vanishes. The situation is analyzed by the control unit that issues a command to the coil of the corresponding contactor and faulty heating element is switched off (patent RU №1828023. Electrothermal de-icing system of the plane circular steps, MCI 64 D 15/12, BI 31, 10.11.1996). The invention adopted for the prototype.
A disadvantage of the known anti-icing system adopted for the prototype, is the use of contactors, the use of a large number of current transformers that produce a large amount of heat, large size and weight.
The objective of the proposed solutions is to reduce the weight and improve the operational reliability of the electrothermal de-icing system by reducing the number and weight of current transformers through the use of operating Wuxi the practical result achievable with the initiated of the claimed invention is to improve flight safety and increase system resource.
This technical result is achieved by the fact that in the known electro-thermal anti-icing system containing teploelectrocental heaters connected to three-phase AC power source through the switching elements, the current transformers, the windings are covered by the supply wires teploelectrocental heaters, the control unit, the outputs of which are connected to control inputs of the switching elements, and the inputs from the windings of the current transformers, in accordance with the proposed technical solution, introduced operational amplifiers through which the windings of the current transformers connected to inputs of the control unit; the switching elements are in the form of a thyristor of keys, each of which is connected to the heater blades; heaters made of length equal to the entire length of the heated surface of the blade; the heaters are made with a variable resistance along the length of the blade; the heaters are made in pairs, each pair connected by a crosspiece at the end of the blade and the butt part is connected to a source of current through thyristor key is testwuide the signal Converter, which are connected with the control unit; the control inputs of thyristor switch connected to the outputs of the control unit corresponding to each ordinal install heaters on all blades in the system blocking key, which is connected through one output of the control unit, and the control input of the blocking key is connected to the Converter temperature sensor.
Given the applicant an analysis of the level of technology has allowed to establish that the analogs are characterized by the sets of characteristics is identical for all features of the declared electrothermal de-icing system, no. Therefore, the claimed technical solution meets the condition of patentability “novelty.”
Search results of known solutions in this field of technology in order to identify characteristics that match the distinctive features of the prototype of the characteristics of the proposed technical solution, showed that they do not follow explicitly from the prior art. Of certain of applicant's prior art there have been no known impact provided the essential features of the claimed technical solution of transformations on the achievement of the technical result. Slovene”.
In Fig.1 shows a structural diagram of the de-icing system of Fig.2 - wiring diagram teploelectrocental heaters and thyristor switch; Fig.3 - scan heated surface of the blade with teploelectrocental heaters; Fig.4 is a sequence diagram of the operation of the system.
Electrothermal de-icing system contains teploelectrocental heaters 1, for example, four pieces throughout the length of each of the rotor blades, thyristor 2 is connected in series with each heater, the current transformers 3, the windings of which cover the wires a, b and C, the supply power to the heaters 1, operational amplifiers 4, the inputs of which are connected with the windings of the current transformers 3. Control inputs thyristor switch 2 band heaters with one serial number install them on all the blades are connected with the corresponding output of the control unit 5, and in one of the control circuits of the thyristor keys set the blocking key 6, and the first, second and third inputs of the control unit with the outputs of the operational amplifiers 4. The fifth and sixth inputs of the control unit 5 is connected with icing detector 7 and the temperature sensor 8 through the transducer 9, operated the Torno keys 2 are connected to the three phases A, In and From the AC power source according to the scheme “triangle” (Fig.2). Teploelectrocental heaters 1 are mounted in pairs throughout the length of the blade and connected to the conductors 10 in the end portion of the blade, with each subsequent pair of heaters covers the previous one. Teploelectrocental the heater 1 is made with a variable resistance along the length of the blade (Fig.3).
The power to teploelectrocental heaters 1 of the blades is performed on the sequence diagram (Fig.4).
Anti-icing system works as follows.
The formation of ice on the blades of the icing detector 7 outputs a signal to the control unit 5, which launches anti-icing system on the cyclic activation of the heated blade. From the outputs of the control unit alternately the signals on the control inputs thyristor switch 2, which connect groups of heaters of the same serial numbers on all blades. Thanks to the variable resistance heaters 1 are evenly ice discharge along the entire length of the blade. Depending on the outside temperature, the value of which in the form of a signal from the temperature sensor 8 and preobrazovatelya signal 9 is supplied to the control unit 5, between cycles podklucil between cycles withstands the control unit 5. At temperatures above a given transducer 9 signal of the temperature sensor 8 is activated the blocking key 6, which separates the circuit of one output control unit 5, and exclude from the cycle of heating one heater of each blade. Because structurally, each heater is connected in pairs conductors 10, heating stops evenly on the upper and lower surfaces of the blade. In the process control system health. During normal operation, de-icing system in the windings of transformers 3, you receive the current, which increases operational amplifiers 4 and is supplied to the corresponding inputs of the control unit 5. The presence of a current of a given level is a signal for the normal operation of the heater 1 to the control unit 5. In the event of a short circuit or breakage of the phases in the group of heaters 1 level signal from the operational amplifier 4 becomes less than or drops to zero, the control unit 5 opens the control inputs of thyristor switch 2, thus disabling the faulty heaters from the power source together with a group of heaters. About the presence of failures in the anti-icing system control unit 5 outputs information in Bo the design documentation and prototype.
Claims 1. Electrothermal de-icing system, for example, for the blades of a helicopter containing teploelectrocental heaters connected to three-phase AC power source through the switching elements, the current transformers, the windings are covered by the supply wires teploelectrocental heaters, the control unit, the outputs of which are connected to control inputs of the switching elements, and the inputs from the windings of the current transformers, characterized in that the system entered operational amplifiers through which the windings of the current transformers connected to inputs of the control unit, and the heaters are made in pairs, each pair connected by a crosspiece at the end of the blade, covering the inner pair of heaters. 2. The system under item 1, characterized in that the switching elements are in the form of a thyristor of keys, each of which is connected to the heater blades. 3. The system under item 1, characterized in that the heaters are made of length equal to the entire length of the heated surface of the blade. 4. The system under item 1, characterized in that the coils are constructed with a variable resistance along the length of the blade. 5. The system under item 1, atlasovarian signal, which are connected with the control unit. 6. The system under item 1, characterized in that the control inputs thyristor switch connected to the outputs of the control unit corresponding to each ordinal install heaters on all blades. 7. System PP.1 and 6, characterized in that the system locking key, which is connected through one output of the control unit, and the control input of the blocking key is connected to the Converter temperature sensor.
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