Aircraft engine nacelle anti-icing system with resistive layer

FIELD: transport.

SUBSTANCE: 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.

EFFECT: reduced sizes, increased anti-icing zone.

26 cl, 17 dwg

The object of the present invention is the anti-icing and de-icing engine nacelle of the aircraft, containing the resistive layer.

The object of the present invention is also nacelle of the engine of the aircraft, containing improved device de-icing and optimized acoustic insulation, based on the resistive layer.

Finally, an object of the present invention is a system for de-icing, containing a grid of resistive elements formed separated resistive layers intended for de-icing of aircraft engine nacelles.

Known aerial gondolas, the inner channel which covers the fan and which contain tubular inlet, equipped with a rim, and a Carter fan, equipped with the first inner tubular part acoustic insulation, while the air intake is connected to the crankcase ventilator tubular transition part.

The removal of ice on the intake and the rim is usually carried out by supplying the intake of hot air coming out of the reactor through pipes or channels made in the thickness of the gondola.

The technical problem is that the supplied hot air in some conditions the x flight has a very high temperature (up to 600°C), and in that the tubular part or tubular parts acoustic insulation made of composite materials that are incompatible with such temperatures.

Combating icing is particularly necessary during the landings of the aircraft and, in particular, during long periods of time when the engines are idling. In such cases, the air temperature in ducts for supplying hot air is low and requires the creation of a powerful air stream.

This calculation suggests that on the contrary, when the ambient temperature is high and when the engine is running at full gas, if the valve control anti-icing airflow is open, the air is heated to the above-mentioned high temperatures. This occurs in particular when the valve is locked in the open position to maintain flight in case of failure of the control valve.

The decrease in air temperature on the phase of flight, when you should avoid too high temperatures, is a very complex task, as known from the prior art heating systems de-icing must be designed in such a way as to protect the engine from freezing in phases when it is operating in the idling conditions, and to cool the air in special circumstances that require cash is being difficult bulky and heavy equipment (heat exchanger, valve, regulator and other elements).

Therefore, in the prior art zone acoustic insulation, heat-sensitive, preferably separate from the zone of protection from icing, and for this transition tubular part includes a coupling zone between the air intake and a Carter fan, not containing the anti-icing to delay the tubular part, equipped with acoustic insulation, from heated parts.

This design creates, in particular, two problems, the first of which is the fact that the annular cross section of the air intake does not contain sound-proofing material, which reduces the effectiveness of these tools reduce noise, and the second is that it is a circular cross-section and does not contain the anti-icing and therefore prone to the formation and accumulation of ice.

The system of de-icing in accordance with the present invention is the provision of opportunities for convergence and even overlap acoustic isolation zones and protection from freezing, it also enables to reduce the power loss of the engine taking into account the fact that in case of engine civil aircraft of conventional power known from the prior art thermal protection system icing OTB who plays the power is about 60 - 80 kW of engine power, not being equipped with real means of regulation or limitation.

The device de-icing in accordance with the present invention can significantly reduce and even eliminate the transition ring section and to bring together and even provide overlapping de-icing part and sound the part to increase as the surface anti-icing, and the surface equipped with noise reduction.

In addition, the device de-icing in accordance with the present invention, located on the surface, does not require complex systems of channels and valves.

In addition, known from the prior art air system allows for protection against icing, but do not allow for simple and effective fight against icing, while the system in accordance with the present invention allows clear of ice separate areas by temporary supply power required for de-icing, while power consumption is determined depending on the selected modes of anti-icing and de-icing.

The present invention proposes a system de-icing and anti-icing, doesn't take up space inside the gondola, potreblyaemaya power and provides greater flexibility by adapting power to fight for flight icing conditions and ground conditions.

In this regard, an object of the present invention is a system de-icing and anti-icing engine nacelle of the aircraft, containing the air intake is equipped with a rim, which is tubular part of the intake that contains the first panel acoustic insulation, characterized in that it includes means for de-icing, containing at least one grating of the heating resistive elements, immersed in insulating material, with anti-icing is made in the form of a layer containing resistive elements in the thickness of the rim of the inlet.

According to the private version of the implementation in accordance with the present invention offers a nacelle of the engine of the aircraft, containing the air intake is equipped with a rim, which is tubular part of the intake that contains the first panel acoustic insulation, characterized in that the rim is equipped with anti-icing, which includes means for de-icing, containing at least one grating of the heating resistive elements, immersed in insulating material, with anti-icing is made in the form of a layer containing resistive elements in the thickness of the rim in which duhozanye, this grid forms part of the wall of the rim, blocking part of the contour, internal to the air intake, and performed, on the one hand, at least part of the contour, the outer towards the inlet, and, on the other hand, at least in the zone of interface between the rim and the first panel acoustic insulation of the tubular part of the inlet.

In particular, the air intake is segmented into a sequence of sectors de-icing, forming a sequence of sublattices, managed at least one control circuit, configured to implement either sequential heating sectors, or simultaneous heating of certain sectors.

According to a preferred variant implementation of the present invention, the system de-icing includes means for de-icing, comprising at least two arrays of heating resistive elements, immersed in insulating material, with at least two rows of resistive elements mentioned gratings separated in such a way as to form two separate grids included in column purified ice panel.

Preferably, the system de-icing in accordance with the present invention includes a control circuit lattices, the content is the following two independent channels, providing the control of the electric power of the two resistive grids.

The object of the present invention is also a method of controlling the system de-icing and anti-icing air intake of the engine nacelle of the aircraft, characterized in that the inlet segment to the sequence of sectors de-icing and control the sequence of resistive grids that are in sectors struggle with icing, using at least one control circuit, implemented with the possibility of simultaneous or sequential supply power to the mentioned sector.

In addition to the gain in flexibility provided by the system in accordance with the present invention, such a system can also improve the acoustic insulation of air ducts, made of composite materials, because this system is not exposed to high temperatures, even in the case of idling conditions.

Other distinctive features and advantages of the present invention are evident from the following descriptions are not limiting example of implementation of the invention given with reference to the drawings, in which:

Fig. 1 - General view of the local section of the engine nacelle of the aircraft.

Fig. 2 is a schematic view of the front section is the first part of the gondola, known from the prior art.

Fig. 3 is a schematic view in section of the front part of the nacelle according to the first embodiment of the present invention.

Fig. 4 is a schematic view in section of the front part of the nacelle according to the first variant implementation of the present invention.

Fig. 5 is a schematic view in section of the front part of the nacelle according to the second variant of implementation of the present invention.

Fig. 6 is a schematic view in section of the front part of the nacelle according to the third variant of implementation of the present invention.

Fig. 7A is a view in section of resistive grids according to a variant of the invention.

Fig. 7B is a detailed view of the grating shown in Fig. 7A.

Fig. 8A, 8B and 8C is a schematic view of the sectors of air intake, air de-icing in accordance with the present invention.

Fig. 9A and 9B is a schematic showing two modes of the system de-icing in accordance with the present invention.

Fig. 10 two examples of the implementation of systems for de-icing in accordance with the present invention.

Fig. 11A and 11B are two examples of cycles of operation of the system de-icing in accordance with the present invention.

The present invention mainly relates to combating icing and protecting against icing parts aircraft is in and in particular, the engine nacelles of these aircraft.

The nacelle 1 of the engine of the aircraft is shown schematically in Fig. 1.

This gondola 1 contains the inlet 2, is equipped with a rim 3, followed by a tubular part 4 of the inlet.

The front part of the gondola, known from the prior art shown in Fig. 2, where it is seen that the tubular part 4, containing a panel acoustic insulation shifted backward relative to the flanges 3 of the air intake, through which is formed a buffer zone between protected from icing part in front of the inner walls 14, and a part containing the panel 5 acoustic insulation, thus to protect the panel from the high temperature thermal device de-icing, conventionally shown as channel 15.

According to examples of the present invention shown in Fig. 3, 4 and 5, the nacelle also comprises a tubular part, equipped with the first panel 5 acoustic insulation of composite materials, and, according to the invention, the rim equipped with means 6, 6A, 6b, 6c, 6d de-icing, forming part of the wall contour, and replacement thermal anti-icing.

Anti-icing in accordance with the present invention cover portion 3b of the contour, is you against the intake, and performed, on the one hand, on part 3A of the rim, the exterior with respect to the inlet, and, on the other hand, in zone 7a, 7b, 7c of coupling between the rim and the tubular part of the inlet.

In particular, according to the example implementation shown in Fig. 3, area 7a of the pair contains the front end 8 of the tubular part of the intake fixedly connected with the inner side of the continuation of the rim 3, the funds 6C de-icing overlap mentioned front end 8.

The tubular part 4 of the composite material contains an outer casing 4A and the inner shell 4b covering the sound insulating material, forming first mentioned panel 5 acoustic insulation, and the front end 8 is formed of the compressed flange of the inner and outer shells 4A, 4b, these short sides connected by means of adhesive or by hot polymerization resin, impregnating shell 4A, 4b, what is known of the ways to perform composite acoustic panels, for example, described in document EP 0 897 174 A1.

According to the example shown in Fig. 4, the rim 3 comprises upper hood 10 forming the upper surface 12 of the intake and extended beyond the front edge 11 of the rim, while the tubular part 4 of the air intake is equipped with a first acoustic panel, double-ring and, extended with the formation of the lower surface 13 of the rim 3. According to this example, the de-icing, forming part of the wall contour, contain the first layer 6A deposited on the inner wall of the upper hood 10, and a second layer deposited on the outer side of the panel 5 acoustic isolation of the elongated parts of the air intake, this area 7b of the pair is approximately level with the front edge 11 of the rim 3.

The advantage of this design is to obtain a continuous zone of acoustic isolation from the internal space of the engine to the level of the leading edge contour that exclusively helps reduce noise.

According to the example shown in Fig. 5, the rim 3 is formed by elongation of the tubular part of the intake, which forms the bottom surface 13, the front edge 11 and the upper surface 12 of the rim 3.

According to the example shown in Fig. 6, which preserved the original design of the air intake shown in Fig. 2, the means 6d de-icing is outside the zone pair, overlapping at least part of the tubular part of the inlet.

Means 6A de-icing close the outer zone 3A of the rim, means 6b close internal zone 3b contour, in this case the equipment is downnow first area 9 acoustic insulation, means 6P closed area 7C of coupling between the rim and the air inlet, and means 6d close of the second zone 5 acoustic isolation.

Shown are means 6, 6A, 6b, 6c, 6d de-icing are electrical means and, in particular, contain a layer that includes a heating resistance.

To protect this layer is preferably placed on the inner surface contour of at least part of the end or leading edge contour. If anti-icing should cover panel acoustic insulation, they, on the contrary, is disposed on the outer surface of the panel and carry out the holes, to ensure that the work of the panel, acoustic insulation, leaving part of the open surface area corresponding to the desired acoustic isolation.

The present invention is intended in particular for use on the nacelles of aircraft containing parts made of composite materials and, in particular, in which the tubular part 4 of the vent panel 5, 9 acoustic insulation made of composite materials.

In the performance of electrical equipment de-icing device configured to operate as an anti-icing, to prevent formation of ice on the protected surfaces, or in the mode of oribi with icing with removing ice, formed on the surface.

Such a device and system, and their operation is described with reference to Fig. 7A - 11B.

As was disclosed above and, in particular, in the case of gas turbine engines of the type known technology used for systems de-icing, is the selection of air power by the engine for supplying hot air through pipelines to the protected zones.

This technology is based on the presence of air power, taken from the traction power of the engine, valve control devices and electrical systems control these valves and the availability of sufficient space for laying pipelines in the gondola.

In contrast to these complex known technical solutions proposed system contains electric heating elements included in the thickness of the panels forming the rim 3 of the air intake and the tubular part of the vent, forming a system of de-icing gondola 1 engine of the aircraft, containing the inlet 2, is equipped with a rim 3.

As shown in Fig. 7A, the electrical heating elements forming means 6, 6A, 6b, 6c, 6d de-icing, formed of at least one grating of the heating resistive elements 102, immersed in insulating material 101, with a means of combating obiedent the eat made in the form of a layer 103A, 103b, which includes resistive elements 102 in the thickness of the rim of the air intake between the generators of its panels 104, 105.

The grid of resistive elements 102 contain a heating electrical resistance that dissipates electrical power through the Joule effect, immersed in insulating material 101.

Anti-icing are either metal resistive elements, for example, made of copper, or composite resistive elements, for example, elements of carbon.

An electrical insulator covering the resistive elements is a soft material, in particular, the type of silicone or neoprene.

As shown in Fig. 7B, the resistive elements 102 are connected in parallel, which limits the risk of a drop in the efficiency of the system in the event of a rupture element, for example, in the collision of the foreign object with the intake.

Each resistive element 102 is separated from adjacent elements by a distance sufficient to provide the necessary electrical insulation (typically of the order of 2 mm for the normal DC or AC voltage from 0 to 400 V).

In addition, as shown in Fig. 7A, lattice heating resistive element 102 is duplicated, forming two separate gratings 103A, 103b, included in the interior of the contour.

is this double construction of lattices provides, in case of failure of one of the gratings, anti-icing is provided in a reduced mode of the other arrays.

To manage these gratings presented system contains circuitry 106, a, 106b control grids containing two independent channels, providing independent control of electric powered two resistive grids 103A, 103b. This control circuit is shown schematically in Fig. 10, while the example cables 108A, 108b, 108c, 108d power, which avoids the location of the cables in the most open bottom area of the inlet shown in Fig. 8B and 8C in separation of air intake into four sectors, forming a four sublattice 201, 202, 203, 204.

Indeed, for safety and, in addition, to optimize the power consumption by the system, the invention provides for the separation of the air intake on the sequence of sectors de-icing, which in Fig. 8A form a sequence of arrays 201, ..., 212, managed independently, at least one circuit 106, 106a, 106b, made with the possibility for consistent heating sectors, or with the ability to simultaneously supply power to a few sectors.

Cables 108A, 108b, 108c, 108d contain the inputs and outputs of electric current through them is as sector.

In Fig. 8A shows four sections, with section 301 corresponds to the connection to the cockpit, section 302 is a section in the engine pylon, where the box 107a and 107b control periods or cycles of the system, section 303 contains a backbone cables between the pylon engine and air intake, and section 304 corresponds to the intake.

The power that must be dispelled in order to achieve the correct mode frost protection depends on the position of the heating element in the air intake, the most critical area of the profile is the inner part of the air intake from the front edge of the contour.

To ensure the function of anti-icing of such a zone dissipated power is constantly supplied with power of 1.5 W/cm².

For less critical areas of operation de-icing, based on periodic heating of the surfaces, though, and assumes an instantaneous scattering of the higher power of the order of 2 to 3 W/cm²however, you can restrict the power consumption of the entire system.

In this mode, de-icing circuit or the control circuit is configured to power-up and power-down on the gratings 103A, 103b or sublattices 201, ..., 212, according to the defined time cycles until the data in Fig. 11A and 11B.

The timing cycle shown in Fig. 11A, contains the passage of current in the resistive element during the time interval t0-T3, including the phase P1 temperature increases, the phase P2 at 0°C ice melting, phase P3 raise the temperature to high values. After that, the circuit is opened, which corresponds to the phase P4 cooling.

In Fig. 11B shows the cycles for all sectors, while the phase of the electric power for heating resistive elements are executed sequentially.

Work in this mode, de-icing in areas of intake helps to compensate for the malfunction of one of the schemes and to maintain a sufficient efficiency of de-icing.

The control circuit of the system shown in Fig. 10, under two separate schemes a, 106b contains a number of cable harnesses 108 powering all resistive sublattice.

These bundles form an independent channels connected to separate boxes 107a, 107b or United with a single control unit, which, in turn, are connected by a bus 115 unit 133 controls and communications with side panel 114 devices for displaying operating parameters and control system.

As mentioned above, the power grids heaters gondolas by means of two independent cable networks 106, 108a, 108b, 108c power and two dedicated sets of elec the historical connectors.

Cables each network laid out in such a way as to be completely independent from other cables network that minimizes the risks of General average schemes.

This system optimizes the power consumption due to the fact that the control circuit is arranged to supply and cut off power to the heaters according to certain time cycles depending on the phase of flight or of the conditions of use of the system.

The block or blocks 107a, 107b, providing control for cable networks and resistive heaters, ensure that the voltage and current will comply with the required values, and the control system is made by detecting the absence of a short circuit or untimely tripping schemes.

Similarly, the circuit blocks, for example, through a power bus connected to the sources 116A, 116b DC voltage and springs 117a, 117b AC voltage, are independent. In addition, to increase the redundancy of each unit is powered by two independent power rail.

At some point each channel or block uses the same bus electrical power, so that if the problem of electrical isolation between the two gratings heaters malfunction affected only one of the power bus.

In particular, in case of malfunction onethe power bus on one of the blocks or channels both block or channel use a different power bus.

To control the system in accordance with the present invention the inlet segment to the sequence of sectors de-icing and control the sequence of resistive grids 201, ..., 212, located in sectors struggle with icing, using at least one schema 106, a, 106b management made with the possibility of simultaneous or sequential supply power to the mentioned sector.

Depending on the location of the sublattices preferably you can choose the mode of de-icing or anti-icing.

Phase 110 anti-icing is carried out by continuous operation, at least one sector de-icing, while phase 111 de-icing is carried out with the help of periodic heating cycle, at least one sector.

In Fig. 9A shows the mode of operation in which the outer part of the gondola processed in the de-icing by successive power-on sector and in which the end flanges of the intake and the tubular portion of the air intake processed in mode frost protection by continuously supplying power to the resistive grid in this part.

In Fig. 9B shows the mode of operation in which the outer part of the gondola and the tubular part of osduhs is barnica power mode de-icing, and only at the end of the contour air intake power mode frost protection.

The present invention is not limited to the examples presented, and, in particular, the modes can be changed by choosing accordingly the mode of operation for the anti-icing mode or for de-icing, depending on flight conditions, from the state of the system or available power, while the divided lattice can be separated from each other in the lateral direction for overlapping successive zones, as shown in Fig. 7B, zones, separated from each other or are located one above the other, or arranged in combination.

1. Gondola (1) of the engine of the aircraft, containing the inlet (2), equipped with a rim (3), which is a tubular part (4) air intake containing the first panel (5) acoustic insulation, characterized in that the rim (3) is equipped with the system de-icing and anti-icing, which contains means (6, 6A, 6b, 6C, 6d) de-icing formed of at least one grating of the heating resistive elements (102), immersed in insulating material (101), anti-icing is made in the form of a layer (103A, 103b), containing resistive elements (102) in the thickness of the rim of the air intake is, the system forms part of the wall of the rim, blocking part (3b) of the contour, internal to the air intake, and performed, on the one hand, at least in part (3A) of the contour, the outer towards the inlet, and, on the other hand, at least in the zone (7a, 7b, 7 C) of coupling between the rim and the first panel (5) acoustic isolation of the tubular part of the inlet.

2. Gondola (1) aircraft engine according to claim 1, wherein each resistive element (102) is separated from adjacent elements by a distance sufficient to provide electrical isolation between elements.

3. Gondola (1) aircraft engine according to claim 1, characterized in that the insulating material covering the resistive elements is a soft material, in particular, the type of silicone or neoprene.

4. Gondola (1) aircraft engine according to one of claims 1 to 3, characterized in that the zone (7a, 7b, 7C) of the pair contains the front end (8) of the tubular part of the intake fixedly connected with the inner side of the continuation of the contour (3), means (6C) de-icing cover mentioned the front end (8).

5. Gondola (1) aircraft engine according to one of claims 1 to 3, characterized in that the tubular part (4) is made of composite materials and includes an outer casing (4A) and the inner is bolocco (4b), covering the sound insulating material, forming first mentioned panel (5) acoustic insulation, while the front end (8) is formed by the compressed flange of the inner and outer shells (4A, 4b).

6. Gondola engine aircraft according to one of claims 1 to 3, characterized in that the second panel (9) of acoustic insulation is located on part (3b) of the contour, internal to the air intake.

7. Gondola (1) aircraft engine according to one of claims 1 to 3, characterized in that the rim (3) contains the upper engine (10), forming the upper surface (12) intake and extended beyond the front edge (11) of the rim, with a tubular part (4) air intake equipped with the first panel acoustic insulation, extended to form a part of the lower surface (13) of the rim (3).

8. Gondola (1) aircraft engine according to one of claims 1 to 3, characterized in that the rim (3) is formed by elongation of the tubular part of the air intake elongated to form the bottom surface (13), the front edge (11) and top surface (12) of the rim (3).

9. Gondola (1) aircraft engine according to one of claims 1 to 3, characterized in that the means (6d) de-icing are at the limit of the zone pair, overlapping at least a portion of the first panel (5) acoustic isolation of the tubular part of the air intake and the implementation of the ENES holes, ensuring the work of the panel, acoustic insulation, leaving an open area sufficient to provide the desired level of acoustic insulation.

10. Gondola (1) aircraft engine according to one of claims 1 to 3, characterized in that the tubular part (4) of the vent panel (5, 9) acoustic insulation made of composite materials.

11. The system de-icing and anti-icing engine nacelle of the aircraft, containing the inlet (2), equipped with a rim (3), which is a tubular part (4) air intake provided with a first panel (5) acoustic insulation, characterized in that it contains means (6, 6A, 6b, 6c, 6d) de-icing formed of at least one grating of the heating resistive elements (102), immersed in insulating material (101), while anti-icing is made in the form of a layer (103 and, 103b), containing resistive elements (102) in the thickness of the rim of the air intake, the air intake is segmented into a sequence of sectors de-icing, forming a sequence of sublattices (201, ..., 212), managed at least one circuit (106, a, 106b) control performed with the opportunity for consistent heating sectors, or with the possibility of simultaneous podicipedidae on some sectors.

12. The system de-icing according to claim 11, characterized in that the control circuit is arranged to supply and cut off power to the grids (103A, 103b) or sublattices (201, ..., 212) according to certain time cycles (109).

13. The system de-icing according to item 12, characterized in that it contains two independent control circuits.

14. The system de-icing according to item 13, wherein the control circuits are grouped in a single control unit.

15. The system de-icing according to any one of § § 11 to 14, characterized in that the circuit or the control circuit contain blocks (107a, 107b) control, are designed to ensure monitoring of resistive grids and supply them with cables (108), and means for measuring values of voltage and current and measuring the absence of a short circuit or untimely tripping schemes.

16. The system de-icing and anti-icing engine nacelle of the aircraft, containing the inlet (2), equipped with a rim (3), which is a tubular part (4) air intake provided with a first panel (5) acoustic insulation, characterized in that it contains means (6, 6A, 6b, 6c, 6d) de-icing formed of at least one grating of the heating resistive elements (102), porogen the x in the insulating material (101), this means de-icing is made in the form of a layer (103A, 103b), containing resistive elements (102) in the thickness of the rim of the inlet, characterized in that it contains means (6, 6A, 6b, 6c, 6d) de-icing formed of at least two arrays of heating resistive elements (102), immersed in insulating material (101), with at least two rows of resistive elements mentioned gratings separated in such a way as to form two separate grids (103A, 103b), included in column protected from icing panel.

17. The system de-icing according to item 16, wherein each resistive element (102) is separated from adjacent elements by a distance sufficient to provide electrical isolation between elements.

18. The system de-icing according to item 16 or 17, characterized in that at least some of the resistive elements (102) are separated gratings are connected in parallel.

19. The system de-icing on p, characterized in that it contains circuits (106, a, 106b) control grids containing two independent channels that control the electric power of the two resistive grids (103A, 103b).

20. The system de-icing according to claim 19, characterized in that the independent channels are grouped into a single unit of management is to be placed.

21. The system de-icing according to item 16 or 17, characterized in that it is made in the gondola (1) of the engine of the aircraft, containing the inlet (2), equipped with a rim (3), which is a tubular part (4) of the air intake, the air intake is segmented into a sequence of sectors de-icing, forming a sequence of sublattices (201, ..., 212), managed at least one circuit (106, a, 106b) control performed with the opportunity for consistent heating sectors, or with the ability to simultaneously supply power to some sectors.

22. The system de-icing according to item 21, wherein the control circuit is configured to independent feeding and disable power grids (103A, 103b) or sublattices (201 ..., 212).

23. The system de-icing according to item 16 or 17, characterized in that the circuit or the control circuit contain blocks (107a, 107b) control, are designed to ensure monitoring of resistive grids and supply them with cables (108), and means for measuring values of voltage and current and measuring the absence of a short circuit or untimely tripping schemes.

24. The way the control system de-icing and anti-icing air intake of the engine nacelle is maternova apparatus according to any one of claims 1 to 3, characterized in that the inlet segment to the sequence of sectors de-icing and control the sequence of resistive grids (201, ..., 212), in sector de-icing, using at least one schema (106, a, 106b) control performed by simultaneous or sequential supply power to the mentioned sector.

25. The way the control system de-icing and anti-icing according to paragraph 24, wherein the exercise phase (110) protection from freezing by means of continuous operation, at least one sector de-icing.

26. The way the control system de-icing and anti-icing on A.25, characterized in that the implement phase (111) de-icing through periodic cycle of heating at least one sector.