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 one piece of aeronautic equipment 100 comprising at least one part intended to be arranged at a skin 27 of the aircraft together with means for fastening on said skin outside the aircraft and means for heating the part. The fastening means comprises tubular tabs 101, 102. The heating means comprises a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates. The closed circuit comprises an evaporator associated with means forming a heat source arranged inside the aircraft and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with an empty section, at least partially formed in the tubular tabs 101, 102 of the fastening means.
权利要求：
CLAIMS
1. An aircraft provided with at least one piece of aeronautic equipment, the equipment (25; 100; 110) comprising at least one part (60; 30, 31) intended to be arranged at a skin (27) of the aircraft, and means for fastening on said skin outside the aircraft and means for heating the part, characterized in that the fastening means comprise means in the form of tubular tabs (101, 102; 111, 112, 113, 114), 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 means forming a heat source arranged inside the aircraft 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, at least partially formed in the tubular tabs (101, 102; 111, 112, 113, 114) of the fastening means.
2. The aircraft according to claim 1, characterized in that the channel (39) is configured for the fluid to circulate therein by capillarity.
3. The aircraft according to claim 1, characterized in that it comprises a circulation pump (45) for the heat transfer fluid.
4. 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).
5. The aircraft according to one of claims 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).
©. 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.
7. The aircraft 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 aircraft 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 aircraft according to one of the preceding claims, characterized in that the heating means comprise at least two tubular tabs (101, 102; 111, 112, 113, 114) whereof the inner duct forms the channel of the circuit.
10. The aircraft according to one of the preceding claims, characterized in that it comprises an aerodynamic measuring probe (30; 100; 110).
11. 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) with tabs (101, 102; 111, 112, 113, 114), produced using an additive manufacturing method and in which the tubular channel (39) with an empty section is produced.
12. 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 10, 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.