Avionic equipment heating

Patent metadata

Field	Value
Publication number	US-10183753-B2
Application number	US-201615220481-A
Country	US
Kind code	B2
Filing date	Jul 27, 2016
Priority date	Jul 28, 2015
Publication date	Jan 22, 2019
Grant date	Jan 22, 2019

Abstract

A piece of aeronautic equipment intended to equip an aircraft, the equipment ( 25 ) including a part intended to be arranged at a skin ( 27 ) of the aircraft and elements for heating the part, characterized in that the heating elements include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator ( 14 ) associated with functional elements ( 25 a ) 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, and in that outside the evaporator ( 14 ), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

First claim

The invention claimed is:

1. A piece of aeronautic equipment configured to equip an aircraft, the aeronautic equipment comprising a part configured to be arranged at a skin of the aircraft and heating means for heating the part, wherein the heating means comprise a thermodynamic loop comprising a closed circuit in which a heat transfer fluid circulates, the closed circuit comprising an evaporator associated with a component of the aeronautic equipment, the component forming a heat source configured to emit heat by emission of heat during operation of the component, and a zone in which a condensation of the heat transfer fluid can occur in an appendage to heat the heat transfer fluid, and outside the evaporator, the circuit in which the fluid circulates is formed by a tubular channel with a hollow cross-section.

2. The aeronautic equipment according to claim 1 , wherein the tubular channel is configured for the heat transfer fluid to circulate therein by capillarity.

3. The aeronautic equipment according to claim 1 , further comprising a circulation pump for circulating the heat transfer fluid.

4. The aeronautic equipment according to claim 1 , wherein the tubular channel forms a single thermodynamic loop outside the evaporator.

5. The aeronautic equipment according to claim 1 , wherein the tubular channel forms plural thermodynamic loops in which the heat transfer fluid circulates in parallel outside the evaporator.

6. The aeronautic equipment according to claim 1 , wherein said part is configured to be at least partially flush with the skin of the aircraft.

7. The aeronautic equipment according to claim 1 , wherein said part is an element configured to be arranged protruding relative to the skin of the aircraft.

8. The aeronautic equipment according to claim 7 , further comprising a base configured to fasten the piece of aeronautic equipment on the skin of the aircraft, wherein the element is arranged on a first side of the base and the evaporator is arranged on a second side of the base, opposite the first side.

9. The aeronautic equipment according to claim 1 , wherein the component of the aeronautic equipment is formed by a portion of the aeronautic equipment or an electronic board of the aeronautic equipment making it possible to contribute heat energy to the evaporator.

10. The aeronautic equipment according to claim 1 , wherein the component of the aeronautic equipment is formed by an actuator thereof.

11. The aeronautic equipment according to claim 1 , wherein the component of the aeronautic equipment is formed by a portion of the aeronautic equipment or an electrical equipment of the aeronautic equipment.

12. The aeronautic equipment according to claim 1 , further comprising an aerodynamic measuring probe.

13. A method for producing a piece of aeronautic equipment according to claim 1 , the equipment comprising a body in which the tubular channel with a hollow cross-section is produced using an additive manufacturing method.

14. A non-transitory storage means storing a data file able to be loaded in a memory of a processing unit associated with an additive manufacturing machine able to manufacture an object by superimposing layers of material, wherein the data file comprises data for three-dimensional depiction of the piece of equipment according to claim 1 , so as to allow, when the data file is loaded into the memory of, and processed by, said processing unit, the manufacture of said piece of equipment by said additive manufacturing machine.

Assignees

• Thales Sa

Inventors

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

Classifications

• B64D15/12 Primary

  by electric heating (heating arrangements specially adapted for transparent or reflecting areas H05B3/84) · CPC title

• B64D15/06 Primary

  Liquid application · CPC title

• F28D2021/0021

  for aircrafts or cosmonautics · CPC title

• B64F5/00

  Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for · CPC title

• B64D33/08

  of power plant cooling systems · CPC title