De-icing device for de-icing a wall of an aircraft to be de-iced and aircraft equipped with such a device

Abstract

A de-icing device for de-icing a wall of an aircraft to be de-iced, comprising a heat source remotely arranged with respect to the wall to be de-iced and at least one closed circuit configured for carrying a heat transfer fluid between the heat source and the wall to be de-iced, the closed circuit comprising: at least one portion facing, in contact with or positioned in the wall to be de-iced, said at least one portion being made of a material permeable to electromagnetic fields; at least one condenser facing, in contact with or positioned in the wall to be de-iced, in which the heat transfer fluid condenses, thereby generating energy in the form of latent heat transmitted to the wall to be de-iced; at least one evaporator facing, in contact with or positioned in the heat source, in which the heat transfer fluid evaporates, thereby absorbing energy in the form of latent heat from said heat source. The application also relates to an aircraft equipped with said de-icing device.

Description

TECHNICAL FIELD

[0001] The present application relates to a surface de-icing device configured to not generate electromagnetic interference. BACKGROUND

[0002] There is a need to de-ice certain surfaces of an aircraft in order to limit the appearance and / or accumulation of ice.

[0003] According to a first embodiment described in document FR 2954280 and for de-icing the inlet of a nacelle of an aircraft and the structure of a wing, the de-icing device comprises at least one source of hot air, at least one injection system for injecting the hot air discharged from the source in the vicinity of the surface to be de-iced, and at least one string of pipes for transporting the hot air from the source of hot air to the injection system.

[0004] According to this first embodiment, the hot air is discharged from a compression stage of an engine acting as a source of hot air. Since the hot air transported and injected is at a temperature exceeding 250°C, each string of pipes and each injection system of the de-icing device is made of a metal material resistant to high temperatures.

[0005] The de-icing device according to the first embodiment cannot be used for de-icing surfaces located in the vicinity of systems sensitive to electromagnetic fields, such as radars, probes or antennas, for the reason that the metal parts making up the de-icing device are liable to generate electromagnetic interference.

[0006] According to a second embodiment for a windshield, a small surface or a surface located far from the engine, the de-icing device comprises at least one network of electrically conductive elements fixed against one of the faces of the surface to be de-iced and configured to dissipate heat by the Joule effect.

[0007] The de-icing device according to the second embodiment cannot be used for de-icing surfaces located in the vicinity of systems sensitive to electromagnetic fields, such as radars, probes or antennas, for the reason that the network of electrically conductive elements generates electromagnetic fields liable to disturb the correct operation of the systems sensitive to electromagnetic fields.

[0008] According to a third embodiment described in document FR 2922050 and for de-icing a radome, the de-icing device comprises a hot air generator configured to heat fresh air and deliver the air at a desired temperature, a set of hot air supply pipes configured to transport the air heated by the hot air generator towards the surface of the radome and to diffuse the air in the form of a laminar flow, and a set of return pipes configured to collect the diffused air on the surface of the radome and to transport the air towards the hot air generator.

[0009] This third embodiment is relatively complex to implement, for it is difficult to diffuse hot air in the form of a laminar flow, especially over curved surfaces, and even more difficult to collect the air to reheat it.

[0010] According to a fourth embodiment described in document FR 2631745, the de-icing device comprises a radome having two rigid polycarbonate sheets and a partition wall positioned between the sheets to form passages in which hot air circulates. The radome delimits an enclosure in which the antenna is positioned. The de-icing device also comprises a heating and circulation system configured to heat the air present in the enclosure and inject it into the passages of the radome, the cooled air exiting the passages of the radome being delivered into the enclosure.

[0011] This fourth embodiment is sometimes unsatisfactory under certain conditions, for the air circulating in the radome needs to be at a not too high temperature and needs to be compatible with the material of the radome. In addition, the efficiency of such a de-icing device is not optimal. The present invention seeks to overcome the drawbacks of the prior art. SUMMARY

[0012] To this end, one subject of the invention is a device for de-icing a wall of an aircraft, said device comprising a heat source remotely arranged relative to said wall and at least one closed circuit configured to transport a heat transfer fluid between said heat source and said wall to be de-iced. According to the invention, said closed circuit comprises:

[0013] - at least one portion facing, in contact with or positioned in said wall to be de-iced, said at least one portion being made of a material permeable to an electromagnetic field,

[0014] - at least one condenser facing, in contact with or positioned in said wall to be de-iced and in which said heat transfer fluid condenses, thereby generating energy in the form of latent heat transmitted to said wall to be de-iced, and

[0015] - at least one evaporator facing, in contact with or positioned in said heat source and in which said heat transfer fluid evaporates, thereby absorbing energy in the form of latent heat from said heat source.

[0016] The de-icing device according to the invention makes it possible to de-ice a wall effectively, without generating an electric current in the vicinity of the wall and without using metal elements in the vicinity of the wall. When the protected wall protects a measuring or communication instrument, the de-icing device contributes to improving the accuracy and / or correct operation of the instrument.

[0017] According to one embodiment, the portion of the closed loop facing the wall to be deiced, in contact with it or positioned in it, is made of composite material.

[0018] According to another feature, the condenser comprises at least one tube extending between an inlet and an outlet of the condenser, forming a serpentine pattern so as to at least partially cover the wall to be deiced.

[0019] According to a first embodiment, the condenser takes the form of a plate made of a material having high thermal conductivity, the plate having two mutually parallel faces, one of the two faces being configured to hold tightly against the wall to be deiced, the one or more tubes being positioned in the plate, between its two faces.

[0020] According to a second embodiment, the condenser is integrated into the wall to be deiced, the one or more tubes being positioned between the faces of the wall to be deiced.

[0021] According to a first configuration, the closed loop is a capillary heat pipe using the capillary effect to return the heat transfer fluid from the condenser towards the evaporator.

[0022] According to a second configuration, the closed loop is a gravity heat pipe using the effect of gravity to return the heat transfer fluid from the condenser towards the evaporator.

[0023] According to another feature, the deicing device comprises a control loop comprising a regulation system for regulating the temperature of the heat source and a sensor configured to measure a characteristic of the heat source and to transmit at least one measurement of the characteristic to the regulation system.

[0024] According to one embodiment, the heat source is an electric heating system and the deicing device comprises an electric power source operated by the regulation system and configured to supply electric power to the electric heating system, the sensor being a temperature sensor configured to measure the temperature of the electric heating system and to transmit at least one measurement of the temperature to the regulation system.

[0025] Another subject of the application is an aircraft comprising at least one measuring or communication instrument protected by a protective wall equipped with a deicing device as indicated above. BRIEF DESCRIPTION OF DRAWINGS

[0026] Further features and advantages will become apparent from the following description of the application, given by way of example only, with reference to the accompanying drawings in which:

[0027] - Figure 1 is a side view of an aircraft,

[0028] - Figure 2 is a diagram of a radome equipped with a de-icing device illustrating an embodiment of the application,

[0029] - Figure 3 is a diagram of a de-icing device illustrating an embodiment of the application,

[0030] - Figure 4 is a diagram of a condenser of a de-icing device illustrating an embodiment of the application, and

[0031] - Figure 5 is a diagram of a regulation system of a de-icing device illustrating an embodiment of the application. DETAILED DESCRIPTION

[0032] As illustrated in Figure 1 , the aircraft 10 has a nose cone 12 in which is housed an element to be protected 14 (visible in Figure 2 ) such as, for example, a radar protected by a protective wall 16 (called radome), the nose cone forming a part of the fuselage of the aircraft 10.

[0033] As depicted in Figure 2 , the protective wall 16 has an external face 16.1 on which the airflow flows and on which ice can form in flight, and an internal face 16.2 facing the element to be protected 14.

[0034] The aircraft 10 comprises at least one de-icing device 18 configured to limit the appearance and / or accumulation of ice on the protective wall 16.

[0035] Of course, the application is not limited to this application. Thus, the de-icing device 18 can be used to limit the appearance and / or accumulation of ice on any protective wall covering a radar, a probe, an antenna or any other measuring or communication element sensitive to a magnetic field and more generally on any wall of the aircraft on which ice can form.

[0036] As illustrated in Figure 2 and Figure 3 , the de-icing device 18 comprises at least one heat source 20 arranged remotely with respect to the protective wall and / or the element to be protected 14, and at least one closed circuit 22 made of a material permeable to electromagnetic fields and thus not generating electromagnetic interference, and in which a heat transfer fluid 24 flows, said closed circuit 22 being configured to transport the heat transfer fluid 24 between the heat source 20 and the protective wall 16.

[0037] Far away means that the heat source 20 is sufficiently far from the element 14 to be protected so that it does not interfere with the correct operation of the element to be protected.

[0038] According to one configuration, the heat source 20 is an electric heating system or hot air, for example hot air emitted from the engines of the aircraft 10 or hot air heated by an electric heating system. The electric heating system means at least one network of electrically conductive elements configured to dissipate heat by Joule effect.

[0039] According to one feature of the application, at least one portion of the closed circuit 22 facing and / or in contact with or positioned in the wall of the protection wall 16 and / or of the element 14 to be protected is made of a material that is transparent to the electromagnetic field and does not generate electromagnetic disturbances.

[0040] For the purposes of the present patent application, two elements are positioned facing each other if they are separated by a distance of less than or equal to 5 cm, which distance does not impair the heat transfer between the two elements.

[0041] According to one embodiment, at least the portion of the closed circuit 22 facing the element 14 to be protected is made of a composite material, for example made of glass or carbon fibers embedded in a thermoplastic or thermosetting resin matrix.

[0042] According to the embodiment visible in Figure 3 , the closed circuit 22 comprises at least one condenser 26 facing, in contact with or positioned in the protection wall 16 to be deiced and in which, in operation, the heat transfer fluid 24 condenses, thus generating energy in the form of latent heat that is transmitted to the protection wall 16, at least one evaporator 28 facing, in contact with or positioned in the heat source 20 and in which, in operation, the heat transfer fluid 24 evaporates, thus absorbing energy in the form of latent heat from the heat source 20, at least one first duct 30 configured to transport the heat transfer fluid 24 from the evaporator 28 towards the condenser 26, and at least one second duct 32 configured to transport the heat transfer fluid 24 from the condenser 26 towards the evaporator 28.

[0043] The first duct 30 comprises a first end 30.1 connected to the outlet 28.1 of the evaporator 28 and a second end 30.2 connected to the inlet 26.1 of the condenser 26.

[0044] The second duct 32 comprises a first end 32.1 connected to the outlet 26.2 of the condenser 26 and a second end 32.2 connected to the inlet 28.2 of the evaporator 28.

[0045] The evaporator 28 is sized according to the temperature range of the heat source 20 and according to the properties of the heat transfer fluid 24 so as to achieve the evaporation of the heat transfer fluid 24 between the inlet 28.2 and the outlet 28.1 of the evaporator 28, the heat transfer fluid 24 being in liquid state at the inlet 28.2 of the evaporator 28 and being in gaseous state at the outlet 28.1 of the evaporator 28.

[0046] The condenser 26 is sized according to the deicing needs and according to the properties of the heat transfer fluid 24 so as to achieve the condensation of the heat transfer fluid 24 between the inlet 26.1 and the outlet 26.2 of the condenser 26, the heat transfer fluid 24 being in gaseous state at the inlet 26.1 of the condenser 26 and being in liquid state at the outlet 26.2 of the condenser 26.

[0047] The energy in the form of latent heat produced during the phase change of the heat transfer fluid 24 in the condenser 26 for deicing makes it possible to use a heat transfer fluid 24 with a lower temperature in the closed circuit 22 and thereby optimizes the efficiency of the deicing device 18.

[0048] By way of indication, the temperature of the heat transfer fluid 24 is less than or equal to 12°C at the source.

[0049] According to one embodiment, the heat transfer fluid 24 is air or methanol.

[0050] According to one embodiment, the condenser 26 comprises at least one tube 34 extending between the inlet 26.1 and the outlet 26.2 of the condenser 26 forming a serpentine pattern so as to at least partially cover the protective wall 16 which can be planar or curved.

[0051] According to one embodiment, the condenser 26 takes the form of a flexible sheet 36 made of a material with high thermal conductivity, the flexible sheet having two mutually parallel faces, one of the two faces being configured to hold tightly against the protective wall 16, the tube or tubes 34 being positioned in the flexible sheet 36 between the two faces thereof.

[0052] According to one configuration, the condenser 26 holds tightly against the internal face 16.2 of the protective wall 16 and is held tightly against the internal face 16.2 of the protective wall, for example by adhesion.

[0053] According to another embodiment, the condenser 26 is integrated in the protective wall 16, the tube 34 being positioned between the internal face 16.1 and the external face 16.2 of the protective wall 16.

[0054] The evaporator 28 can take the form of a heat exchanger.

[0055] In operation, when the heat transfer fluid 24 evaporates in the evaporator 26, this causes a slight increase in pressure, resulting in the natural flow of the heat transfer fluid 24 from the evaporator 28 towards the condenser 26. To ensure the return of the heat transfer fluid 24 from the condenser 26 towards the evaporator 28, one can use the effect of gravity by positioning the condenser 26 at a higher level than the evaporator 28, or the effect of capillarity by using a suitable internal structure of the second duct 32 or by fitting a pump or a circulator on the second duct 32.

[0056] According to one embodiment, the closed circuit 22 is a capillary heat pipe using the capillary effect to return the heat transfer fluid 24 from the condenser 26 towards the evaporator 28, or a gravity heat pipe using the effect of gravity to return the heat transfer fluid 24 from the condenser 26 towards the evaporator 28.

[0057] The de-icing device 18 comprises a regulation system 38 configured to regulate the temperature of the heat source 20 and ultimately the de-icing capacity.

[0058] According to one configuration, the de-icing device 18 comprises a control loop 40 comprising, in addition to the regulation system 38, a sensor 42 configured to measure a characteristic of the heat source 20, more particularly its temperature, and to transmit at least one measurement of this characteristic to the regulation system 38.

[0059] According to one embodiment, when the heat source 20 is an electric heating system 44, the de-icing device comprises an electric power source 46 operated by the regulation system 38 and configured to supply the electric heating system 44 and the temperature sensor 42 with electric power, and a temperature sensor configured to measure the temperature of the electric heating system 44 and to transmit at least one measurement of the temperature to the regulation system 38.

[0060] The de-icing device 18 according to the application makes it possible to achieve effective de-icing of the wall without generating electromagnetic interference. In the case where the protected wall 16 protects a measuring or communication instrument, the de-icing device 18 allows to improve the precision and / or correct operation of this instrument against icing problems, which can be impaired by the accumulation of ice or electromagnetic interference in the absence of a de-icing device according to the application.

Claims

1. An ice removal device for de-icing a wall of an aircraft to be de-iced, the ice removal device comprising a heat source (20) and at least one closed circuit (22), the heat source being disposed remotely with respect to the wall to be de-iced (16), the at least one closed circuit having a first duct configured to convey a heat transfer fluid (24) from the heat source (20) towards the wall to be de-iced (16) and a second duct configured to return the heat transfer fluid from the wall to be de-iced (16) to the heat source (20), characterized in that The closed circuit (22) comprises: - at least one portion facing, in contact with or positioned in the wall (16) to be de-iced, made of a material permeable to electromagnetic fields, - at least one condenser (26) facing, in contact with or positioned in the wall (16) to be de-iced, and in which the heat transfer fluid (24) condenses, thus generating energy in the form of latent heat to be transferred to the wall (16) to be de-iced, and - at least one evaporator (28) facing, in contact with or positioned in the heat source (20) and in which the heat transfer fluid (24) evaporates, thus absorbing energy in the form of latent heat from the heat source (20); wherein the heat transfer fluid is gaseous at the inlet of the condenser and liquid at the outlet of the condenser; wherein the heat transfer fluid is liquid at the inlet of the evaporator and gaseous at the outlet of the evaporator.

2. The de-icing device of claim 1, wherein The portion of the closed circuit (22) facing, in contact with or positioned in the wall (16) to be de-iced is made of a composite material.

3. The de-icing device of claim 1, wherein The condenser (26) comprises at least one tube (34) extending between an inlet (26.1) and an outlet (26.2) of the condenser (26), forming a serpentine pattern so as to at least partially cover the wall (16) to be de-iced.

4. The de-icing device of claim 3, wherein The condenser (26) takes the form of a plate (36) made of a material with high thermal conductivity, having two mutually parallel faces, one of which is configured to hold tightly against the wall (16) to be de-iced, the at least one tube (34) being positioned in the plate (36) between its two faces.

5. The de-icing device of claim 3, wherein The condenser (26) is integrated into the wall (16) to be de-iced, the at least one tube (34) being positioned between the faces of the wall (16) to be de-iced.

6. The de-icing device according to one of claims 1 to 5, characterized in that The closed circuit (22) is a capillary heat pipe which uses the capillary effect to return the heat transfer fluid (24) from the condenser (26) towards the evaporator (28).

7. The de-icing device according to one of claims 1 to 5, characterized in that The closed circuit (22) is a gravity heat pipe which uses the effect of gravity to return the heat transfer fluid (24) from the condenser (26) towards the evaporator (28).

8. The de-icing device according to one of claims 1 to 5, characterized in that The de-icing device comprises a control circuit (40) comprising a regulation system (38) for regulating the temperature of the heat source (20) and a sensor (42) configured to measure a characteristic of the heat source (20) and to transmit at least one measurement of the characteristic to the regulation system (38).

9. The de-icing device of claim 8, wherein Said heat source (20) is an electric heating system (44) and said de-icing device comprises an electric power source (46) operated by said regulation system (38) and configured for supplying electric power to said electric heating system (44), said sensor (42) being a temperature sensor configured for measuring the temperature of said electric heating system (44) and transmitting at least one measurement of said temperature to said regulation system (38).

10. An aircraft comprising at least one measuring or communication instrument protected by a protective wall, said protective wall being equipped with a de-icing device according to one of the preceding claims.

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