当前申请(专利权)人地址：
TOUR CARPE DIEM, Place des Corolles, Esplanade Nord, Courbevoie 92400, France (including Overseas Departments and Territories)
摘要：
The invention relates to the heating of a piece of aeronautic equipment intended to be arranged at the skin of the aircraft. The equipment 25 comprises a part 30, 31 intended to be arranged at the skin 27 of the aircraft and means for heating the part. The heating means comprise a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates. The closed circuit comprises an evaporator 14 and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator 14, the circuit in which the fluid circulates is formed by a tubular channel with an empty section. At least part of the equipment is made from a material with a low heat conductivity.
权利要求：
CLAIMS
1. A piece of aeronautic equipment intended to equip an aircraft, the equipment (25) comprising at least one part (60; 30, 31) intended to be arranged at a skin (27) of the aircraft and means for heating the part, characterized in that the heating means comprise a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator (14) and a zone (15) in which a condensation of the heat transfer fluid can occur in the appendage to heat it, and in that outside the evaporator (14), the circuit in which the fluid circulates is formed by a tubular channel (39) with an empty section, and in that at least this part of the equipment is made from a material with a low heat conductivity.
2. The aeronautic equipment according to claim 1, characterized in that the channel (39) is configured for the fluid to circulate therein by capillarity.
3. The aeronautic equipment according to claim 1, characterized in that it comprises a circulation pump (45) for the heat transfer fluid.
4. The aeronautic equipment according to one of the preceding claims, characterized in that the tubular channel (39) forms a single thermodynamic loop (11) outside the evaporator (14).
5. The aeronautic equipment according to one of clams 1 to 3, characterized in that the tubular channel (39) forms several thermodynamic loops (11a, 11b) in which the heat transfer fluid circulates in parallel outside the evaporator (14).
6. The aeronautic equipment according to one of the preceding claims, characterized in that the part (61) is configured to be flush with the skin (27) of the aircraft.
7. The aeronautic equipment according to any one of claims 1 to 5, characterized in that the part is an appendage (30, 31) configured to be arranged protruding relative to the skin (27) of the aircraft.
8. The aeronautic equipment according to claim 7, characterized in that it comprises a base (38) intended to fasten the piece of equipment on the skin (27) of the aircraft, in that the appendage (30, 31) is arranged on a first side of the base (38) and in that the evaporator (14) is arranged on a second side of the base (38), opposite the first side.
9. The aeronautic equipment according to one of the preceding claims, characterized in that the material has a heat conductivity at 50°C below 100 W/m.K.
10. The aeronautic equipment according to claim 9, characterized in that the material has a heat conductivity at 50°C preferably below 60 W/m.K.
11. The aeronautic equipment according to one of claims 1 to 8, characterized in that it includes at least two materials with different conductivities.
12. The aeronautic equipment according to one of claims 1 to 8, characterized in that it includes a material having a conductivity gradient.
13. The aeronautic equipment according to any one of the preceding claims, characterized in that it is made from titanium.
14. The aeronautic equipment according to any one of the preceding claims, characterized in that it comprises an aerodynamic measuring probe (30).
15. A method for producing a piece of aeronautic equipment according to one of the preceding claims, the equipment comprising a body (47) in which the tubular channel (39) with an empty section is produced, the method being characterized in that the body (47) is produced using an additive manufacturing method.
16. A data file stored on storage means and able to be loaded in the memory of a processing unit associated with an additive manufacturing machine able to manufacture an object by superimposing layers of material, characterized in that it comprises data for three-dimensional depiction of the piece of equipment according to any one of claims 1 to 14, so as to allow, when it is loaded into memory
of, and processed by, said processing unit, the mant sé equipment by said additive manufacturing machine.