Thales

Thomson-csf Sextant

Thales Avionics S.a.

Claude Sarno

Romain Hodot

Jean-Philippe Pineau

Frederic Martin

Henri Bouteille

Philippe Oconte

Christian Tantolin

Adrien Desjardins

Bertrand Leverrier

Claude Rougeot

Georges Moulin

Francois Morlet

Marc Duval-Destin

Serge Parbaud

Jean-Yves Catros

Pierre Noel

Jean-Luc Durand

Christophe Jarnias

Pierre Marfisi

This aeronautical equipment for an aircraft, comprising a part configured to be positioned at the level of a skin of the aircraft and means for reheating this part comprising a closed-circuit thermodynamic loop in which a phase-change heat transfer fluid circulates, is wherein it includes means for monitoring the fluid pressure in the loop in order to detect and report a malfunction of the equipment.

Aeronautical equipment

The present invention relates to a thermal control device of a component, the control device including: a power source, a converter able to convert a temperature variation into a resistance variation, and a cooling module including two faces, a first face at a first temperature and a second face at a second temperature, the difference between the first temperature and the second temperature depending on the current supplying the cooling module, the first face being in, contact with the component, the cooling module, the converter and the power source being arranged electrically so that the current supplying the converter decreases with a temperature increase and the current supplying the cooling module remains constant.

Thermal control device of a component, associated electronic system and platform

The present invention relates to an electronic system comprising an electronic system comprising an electromechanical microsystem and a hermetic box encapsulating said microsystem. The box includes a fastening plane. The electromechanical microsystem includes a sensitive part and at least two beams connecting the sensitive part to the fastening plane. The beams are thermally coupled to the sensitive part and are electrically coupled to one another. The system further includes a thermal regulator of the electromechanical microsystem including an electrical circuit including at least two ends connected to the beams, and a circuit controller able to generate an electrical current in the electrical circuit to modify the temperature of the sensitive part.

Electronic system comprising a microelectromechanical system and a box encapsulating this microelectromechanical system

An aerodynamic measurement probe comprises a part to be sited in the region of the skin of an 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 comprising an evaporator and a zone in which the heat-transfer fluid can be condensed in the appendage in order to heat it. Outside the evaporator, the circuit in which the fluid circulates is formed by a tubular duct of open cross section.

Heating of an aerodynamic measurement probe

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.

Heating for an avionic equipment

A heater of a piece of aeronautic equipment is intended to be arranged at the skin of an aircraft. The equipment includes a part intended to be arranged at the skin of the aircraft and elements for heating the part. The heating element include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator 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 part of the equipment is made from a material with a low heat conductivity.

Non conducting material

Manufacturing method by addition for at least one part of a piece of aeronautic equipment intended to equip an aircraft, the equipment piece including at least one part intended to be arranged at a skin of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit at least partially integrated, in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which condensation of the heat transfer fluid can occur in the appendage to heat it, outside the evaporator, the circuit being formed by a tubular channel with an empty section at least partially integral with the equipment piece, at least the part of the equipment piece arranged outside the aircraft is made by additive manufacturing and includes a base for fastening on the skin of the aircraft from which support elements for a Pitot tube extend.

Additive manufacturing method for an avionic equipment

A piece of aeronautic equipment intended to equip an aircraft, the equipment () including a part intended to be arranged at a skin () 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 () associated with functional elements () 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 (), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

Avionic equipment heating

An aircraft provided with at least one piece of aeronautic equipment, the equipment () including a part intended to be arranged at a skin () 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 () associated with functional elements () 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, the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

Aircraft including plane equipment heating with a thermodynamic loop having a closed circuit in which heat transfer liquid circulates and the closed circuit loop including an evaporator

A piece of aeronautic equipment intended to equip an aircraft, the equipment piece () including at least one part intended to be arranged at a skin () outside of the aircraft and heating elements for that part, which include a thermodynamic loop including a closed circuit in which a heat transfer fluid circulates, the closed circuit including an evaporator and a zone in which 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 the part of the piece of equipment arranged outside the aircraft is made by additive manufacturing and includes a fastening base () for fastening on the skin of the aircraft from which support elements () for a Pitot tube () provided with lateral static pressure taps () extend.

Biphase heating

An aircraft provided with at least two pieces of aeronautic equipment, a first piece of equipment () including a part intended to be arranged at a skin () 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 () associated with functional elements () of the second piece of equipment () 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 (), the circuit in which the fluid circulates is formed by a tubular channel with an empty section.

First equipment heating device

The invention relates to the cooling of the item of electronic equipment comprising an electronic compartment formed from a housing and at least one electronic board assembled in the housing. The board is intended to be assembled in a removable manner in the housing by a movement of translation along a groove in order to reach an operating position, the assembly of the board () being carried out through an insertion face of the housing. According to the invention, the item of equipment comprises a heat sink of elongate shape disposed along the groove making it possible to collect the heat emitted by the components and means of extraction of the heat collected by the heat sink, the extraction means being located outside of the electronic compartment.

Cooling an electronic device

A rack for an aeronautical platform comprising two parallel shelves positioned between a front face and a rear face of the platform, the rack being inserted into the platform by translation from the front face to the rear face the rack containing electronic equipment extending primarily in a plane, the electronic equipment being positioned in a useful compartment of the rack and cooled by forced convection. The electronic equipment is positioned in such a way that its main plane is parallel to the shelves. The rack comprises means for guiding an air flow used for the cooling of the electronic equipment item, the air flow penetrating into the useful compartment parallel to the plane of the electronic equipment item and at right angles to the direction of insertion of the rack into the platform.

Rack intended to equip an aeronautical platform

A heat transfer device including a container in which a heat-transfer fluid circulates in a closed loop. The heat transfer fluid is capable of undergoing an increase in volume on solidifying. The container further contains particles suspended in the heat-transfer fluid. At least some of the particles are compressible under the pressure of the fluid, as the fluid is solidifying, so as to at least partially compensate for the increase in volume of the fluid upon solidifying.

Heat transfer device including compressible particles suspended in a circulating heat-transfer fluid

The invention relates to an electromechanical device comprising a package and at least one component surface-mounted in the package, characterized in that it also comprises at least one nanotube-based interface providing a mechanical link for vibratory and thermal filtering between said component and the package. Advantageously, the nanotube-based interface can also serve as an electrical and/or thermal interface with the electrical contacts with which the package is equipped.

Growing community of inventors

Valence, France

Claude Sarno