Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

Abstract: 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.

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.

Abstract: 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.

Abstract: 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.

Abstract: An aluminum alloy powder for additive manufacturing, and method for manufacturing a piece by manufacturing from this powder are disclosed. In one aspect, the alloy powder is composition by weight: AlcompSiaMgbZrcRd wherein R represents one or more elements selected from the group consisting of Mn, Cr, Cu, Zn and Ti, and wherein, in percent by weight: a is between 0.2% and 1%, b is between 0.3% and 1.7%, c is between 0.4% and 5%, and d is between 0% and 1%, wherein the balance consists of aluminum and unavoidable impurities.

Abstract: 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.

Abstract: 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.

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 (25a) 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.

Abstract: An aircraft provided with at least one piece of aeronautic equipment, 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 (70) 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.

Abstract: A piece of aeronautic equipment intended to equip an aircraft, the equipment piece (25) including at least one part intended to be arranged at a skin (27) 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 (120) for fastening on the skin of the aircraft from which support elements (130) for a Pitot tube (140) provided with lateral static pressure taps (150) extend.

Abstract: An aircraft provided with at least two pieces of aeronautic equipment, a first piece of 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 (80) of the second piece of equipment (81) 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.

Abstract: A heating of a piece of aeronautic equipment intended to be arranged at the skin of the aircraft. The equipment (25) includes a part (30, 31) intended to be arranged at the skin (27) 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 (14) and a zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it. Outside the evaporator (14), 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.

Abstract: An aircraft provided with at least two pieces of aeronautic equipment, a first piece of 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 (80) of the second piece of equipment (81) 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.

Abstract: 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 in an appendage, characterized in that the heating elements include elements forming an oscillating heat pipe (90) including at least one evaporator associated with elements forming a heat source and at least one zone in which a condensation of the heat transfer fluid can occur in the appendage to heat it.

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 (25a) 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.

Abstract: The invention relates to an aircraft provided with at least one piece of aeronautic equipment (100), the equipment comprising at least one part 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), 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 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, and 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 tabs (101, 102) of the fastening means.