Surface deicing device configured not to generate electromagnetic interference
A device for deicing a wall of an aircraft, comprising a closed circuit. The closed circuit comprises at least one condenser, positioned in the environment of the wall that is to be deiced, and in which a heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, at least one evaporator positioned in the environment of a heat source sited remotely with respect to the wall, and in which the heat-transfer fluid evaporates, absorbing energy in the form of latent heat coming from the heat source. At least part of the closed circuit is facing, in contact with, or positioned in, the wall that is to be deiced, being made of a material transparent to electromagnetic fields.
1. A device for deicing a wall of an aircraft, comprising:
a heat source sited remotely with respect to the wall,
at least one closed circuit having a first pipe configured to carry a heat-transfer fluid from the heat source to the wall that is to be deiced and a second pipe configured to return the heat-transfer fluid from the wall that is to be deiced to the heat source, the closed circuit comprising:
at least one condenser made from a material that is transparent to electromagnetic fields, the at least one condenser facing, in contact with, or positioned in, the wall that is to be deiced, and in which the heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, and
at least one evaporator facing, in contact with, or positioned in, the heat source, and in which the heat-transfer fluid evaporates, absorbing latent heat energy from the heat source,
wherein the heat transfer fluid comprises, at an inlet of the at least one evaporator, a liquid and, at an outlet of the at least one evaporator, comprises a vapor.
2. The deicing device according to claim 1 , wherein the at least one condenser is made of composite material.
3. The deicing device according to claim 1 , wherein the condenser comprises at least one tube which extends between an inlet and an outlet of the condenser, describing a serpentine so as to at least partially cover the wall that is to be deiced.
4. The deicing device according to claim 3 , wherein the condenser is formed as a plate made from a material having high thermal conductivity, which has two mutually parallel faces, one of which is configured to be held closely against the wall that is to be deiced, the tube or tubes being positioned in the plate between its two faces.
5. The deicing device according to claim 3 , wherein the condenser is integrated into the wall that is to be deiced, the tube or tubes being positioned between the faces of the wall that is to be deiced.
6. The deicing device according to claim 1 , wherein the closed circuit is a capillary heat pipe using a capillary effect to return the heat-transfer fluid from the condenser towards the evaporator.
7. The deicing device according to claim 1 , wherein the closed circuit is a gravity heat pipe using gravity to return the heat-transfer fluid from the condenser towards the evaporator.
8. The deicing device according to claim 1 , wherein the deicing device comprises a control loop which comprises a regulating system for regulating the temperature of the heat source, a sensor configured to measure a characteristic of the heat source and transmit at least one measured value of the characteristic to the regulating system.
9. The deicing device according to claim 8 , wherein the heat source is an electrothermal system, and wherein the deicing device comprises an electric power supply operated by the regulating system and configured to supply power to the electrothermal system, the sensor being a temperature sensor configured to measure a temperature of the electrothermal system and to transmit at least one measured value of the temperature to the regulating system.
10. An aircraft comprising at least one measurement or communication instrument protected by a protective wall equipped with a deicing device according to claim 1 .
11. A device for deicing a wall of an aircraft, comprising:
a heat source sited remotely with respect to the wall, wherein the heat source is an electrothermal system;
at least one closed circuit having a first pipe configured to carry a heat-transfer fluid from the heat source to the wall that is to be deiced and a second pipe configured to return the heat-transfer fluid from the wall that is to be deiced to the heat source, the closed circuit comprising:
at least one condenser made from a material that is transparent to electromagnetic fields, the at least one condenser facing, in contact with, or positioned in, the wall that is to be deiced, and in which the heat-transfer fluid condenses, generating energy in the form of latent heat which is transmitted to the wall that is to be deiced, and,
at least one evaporator facing, in contact with, or positioned in, the heat source, and in which the heat-transfer fluid evaporates, absorbing latent heat energy from the heat source;
a control loop comprising a regulating system for regulating the temperature of the heat source;
a sensor configured to measure a characteristic of the heat source and transmit at least one measured value of the characteristic to the regulating system; and,
an electric power supply operated by the regulating system and configured to supply power to the electrothermal system, the sensor being a temperature sensor configured to measure a temperature of the electrothermal system and to transmit at least one measured value of the temperature to the regulating system.