Heating for an avionic equipment

Patent metadata

Field	Value
Publication number	US-10472074-B2
Application number	US-201615220524-A
Country	US
Kind code	B2
Filing date	Jul 27, 2016
Priority date	Jul 28, 2015
Publication date	Nov 12, 2019
Grant date	Nov 12, 2019

Abstract

The invention relates to an aircraft provided with at least one piece of aeronautic equipment fastened to the outside skin of the aircraft and a heater for heating the piece of aeronautic equipment. The heater is in the form of a thermodynamic closed circuit loop circulating heat-transfer fluid and including an evaporator and a heat source located inside the aircraft and a condenser located in the piece of aeronautic equipment or an appendage thereto. Fasteners in the form of tubular tabs include tubular channels for circulating the heat-transfer fluid.

First claim

The invention claimed is:

1. An aircraft provided with at least one piece of aeronautic equipment, the equipment comprising:
at least one part intended to be arranged at a skin of the aircraft; and
a fastener on said skin outside the aircraft that serves to fasten the at least one part onto the aircraft; and
a heater configured to heat the part;
wherein characterized in that the fastener comprises tubular legs,
wherein in that the heater comprises a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator associated with a heat generator arranged inside the aircraft and a zone in which a condensation of the heat transfer fluid can occur in the at least one piece of aeronautic equipment to heat it, and
wherein in that 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 leg of the fastener,
wherein the empty section of the tubular channel does not include any filling other than the fluid, and
wherein the tubular channel with an empty section at least partially formed in the tubular legs of the fastener comprises an inner duct within the tubular legs.

2. The aircraft according to claim 1 , characterized in that wherein the tubular channel with an empty section at least partially formed in the tubular legs is configured for the fluid to circulate therein by capillarity.

3. The aircraft according to claim 1 , characterized in that wherein the heater comprises a circulation pump for the heat transfer fluid.

4. The aircraft according to claim 1 , characterized in that wherein the thermodynamic loop comprises a single loop.

5. The aircraft according to claim 1 , characterized in that wherein the thermodynamic loop comprises one or more parallel loops.

6. The aircraft according to claim 1 , characterized in that the part comprises an appendage configured to be arranged protruding relative to the skin of the aircraft.

7. The aircraft according to claim 1 , characterized in that wherein the fastener comprises an appendage which further comprises a base intended to come into contact with the skin of the aircraft to allow for fastening the piece of aeronautic equipment on the skin of the aircraft, in that the appendage is arranged on a first side of the base, and wherein the evaporator is arranged on a second side of the base, opposite the first side.

8. The aircraft according to claim 1 , characterized in that wherein the at least one part comprises an aerodynamic measuring probe.

9. The aircraft according to claim 1 , wherein the at least one part comprises an aerodynamic measuring probe with a body and wherein at least two tubular legs among said tubular legs extend on either side of the body of the probe to form a gantry with a roundish gate shape, in a plane perpendicular to the skin of the aircraft and comprising the tubular legs, the roundish gate shape comprising a top, the roundish gate shape having a dimension in a direction parallel to the skin of the aircraft, said dimension being increasing from the top towards the skin of the aircraft.

10. A method for producing a first piece of aeronautic equipment for an aircraft according to claim 1 , the equipment comprising a body with tabs, produced using an additive manufacturing method and in which the tubular channel with an empty section is produced.

11. A data file 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 claim 1 , 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.

Assignees

• Thales Sa

Inventors

• Desjardins Adrien
• Martin Frederic
• Sarno Claude
• Hodot Romain
• Pineau Jean-Philippe

Classifications

• F28D15/043

  forming loops, e.g. capillary pumped loops · CPC title

• F28D15/02

  in which the medium condenses and evaporates, e.g. heat pipes {(heat pipes used in solar heat collectors F24S10/95; in radiators F28D1/0226; in nuclear reactors G21C15/257)} · CPC title

• B64D43/02 Primary

  for indicating aircraft speed or stalling conditions · CPC title

• F28D15/0266

  with separate evaporating and condensing chambers connected by at least one conduit; Loop-type heat pipes; with multiple or common evaporating or condensing chambers (F28D15/043 takes precedence) · CPC title

• G01P5/165

  Arrangements or constructions of Pitot tubes · CPC title