Thales

Romain Hodot

Claude Sarno

Jean-Philippe Pineau

Frederic Martin

Adrien Desjardins

Bertrand Leverrier

Claude Rougeot

Philippe Oconte

Lilian Cauchard

Marc Duval-Destin

A pressure measurement probe for an aircraft, includes a pressure sensor board comprising an electronic board equipped with a pressure sensor provided with an air inlet, the electronic board further comprising at least four fixing points distributed on a circle at regular angular intervals and configured to allow the sensor board to be fixed in the pressure measurement probe in such a way as to have, when the aircraft is on the ground, a pressure sensor air inlet that is directed downward and an angular offset less than or equal to 45° between the axis of the air inlet of the pressure sensor and the vertical, irrespective of the position of the probe on the aircraft.

Pressure measurement probe comprising a pressure sensor board

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.

Growing community of inventors

Valence, France

Romain Hodot