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：
An aircraft is provided with at least two pieces of aeronautic equipment, a first piece of equipment 25 comprises a part intended to be arranged at a skin 27 of the aircraft and means for heating the part. The heating means comprises a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates. The closed circuit comprises an evaporator 14 associated with functional means 80 of the second piece of equipment 81 of the aircraft forming a heat source giving off heat during their operation 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.
权利要求：
CLAIMS
1. An aircraft provided with at least two pieces of aeronautic equipment, a first piece of equipment (25) comprising a 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) associated with functional means (80) of the second piece of equipment (81) of the aircraft forming a heat source giving off heat during their operation 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.
2. The aircraft according to claim 1, characterized in that the functional means of the second piece of equipment (81) of the aircraft forming a heat source are formed by a part or an electronic board thereof.
3. The aircraft according to claim 1, characterized in that the functional means of the second piece of equipment (81) of the aircraft forming a heat source are formed by an actuator thereof.
4. The aircraft according to claim 1, characterized in that the functional means of the second piece of equipment (81) of the aircraft forming a heat source are formed by a part or a piece of electrical equipment thereof.
5. The aircraft according to one of the preceding claims, characterized in that the channel (39) is configured for the fluid to circulate therein by capillarity.
©. The aircraft according to claim 5, characterized in that it comprises a circulation pump (45) for the heat transfer fluid.
7. The aircraft according to one of the preceding claims, characterized in that the tubular channel (39) forms a single thermodynamic loop (11) outside the evaporator (14).
8. The aircraft according to one of claims 1 to 6, 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).
9. The aircraft 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.
10. The aircraft according to any one of claims 1 to 8, characterized in that the part is an appendage (30, 31) configured to be arranged protruding relative to the skin (27) of the aircraft.
11. The aircraft according to claim 10, characterized in that the first piece of equipment 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.
12. The aircraft according to one of the preceding claims, characterized in that the first piece of equipment comprises an aerodynamic measuring probe (30).
13. A method for producing a first piece of aeronautic equipment for an aircraft 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.
14. 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 for an aircraft according to any one of claims 1 to 12, so as to allow, when it is loaded into memory of, and processed by, said processing unit, the manufacture of said piece of equipment by said additive manufacturing machine.