Abstract: A method for manufacturing in space a rigid structure having a lattice is disclosed. The method includes creating of at least two framework elements from a coil of metal strip or wire, and creating of the lattice by cold-connecting the framework elements.

Abstract: A method for manufacturing in space a rigid structure having a lattice is disclosed. The method includes creating of at least two framework elements from a coil of metal strip or wire, and creating of the lattice by cold-connecting the framework elements.

Abstract: Disclosed is a device for controlled separation of a first so-called stationary part and a second so-called mobile part, the stationary part having a stationary connecting surface opposite a mobile connecting surface of the mobile part, the stationary part having a different thermal expansion coefficient from that of the mobile part, the separation device including: at least one connecting agent arranged in a layer between the stationary connecting surface and the mobile connecting surface, at least one device for heating at least one of the stationary part and the mobile part, and at least one system for controlling the heating device.

Abstract: Disclosed is a device for controlled separation of a first so-called stationary part and a second so-called mobile part, the stationary part having a stationary connecting surface opposite a mobile connecting surface of the mobile part, the stationary part having a different thermal expansion coefficient from that of the mobile part, the separation device including: at least one connecting agent arranged in a layer between the stationary connecting surface and the mobile connecting surface, at least one device for heating at least one of the stationary part and the mobile part, and at least one system for controlling the heating device.

Abstract: An anaerobic propulsion device of hybrid type. The propulsion device includes a combustion chamber into which an oxidant is injected thereto comes into contact with a fuel. The chamber includes an orifice, notably a nozzle, to inject the combustion gases. The fuel takes the form of solids divided into granules, typically grains, powder or beads. The propulsion device further includes a segregation device arranged between a reservoir for granules of solid fuel, and the combustion chamber. The segregation device is configured to prevent granules of fuel in solid form from passing between the reservoir and the combustion chamber. The segregation device includes orifices to allow the passage of the fuel, once the fuel has become pasty, liquid or vaporized.

Abstract: A device for cooling at least two distinct heat sources comprises a closed circuit in which a diphasic fluid flows. At least one capillary evaporator is configured to be placed in thermo contact with one of the heat sources, referred to as the primary heat source. Each other heat source referred to as a secondary heat source that is to be cooled. At least one exchanger configured to be placed in thermal contact with the secondary heat source. At least one first condenser positioned downstream of the evaporator, and upstream of the at least one exchanger. At least one last condenser positioned upstream of the evaporator and downstream of the at least one exchanger.

Abstract: The invention relates to a heat transfer system with one main capillary pumped diphasic fluid loop and a secondary capillary pumped diphasic fluid loop suitable for cooling at least one hot source. The main fluid loop and the secondary fluid loop have one evaporator, a vapor pipe capable of conveying the cooling fluid in the vapor state from the evaporator to a condenser, a condenser and a liquid pipe capable of conveying the cooling fluid in the liquid state from the condenser to the evaporator-so that the cooling fluid of the main fluid loop is in heat exchange with the cooling fluid of the secondary fluid loop.

Abstract: An anaerobic propulsion device of hybrid type. The propulsion device includes a combustion chamber into which an oxidant is injected thereto comes into contact with a fuel. The chamber includes an orifice, notably a nozzle, to inject the combustion gases. The fuel takes the form of solids divided into granules, typically grains, powder or beads. The propulsion device further includes a segregation device arranged between a reservoir for granules of solid fuel, and the combustion chamber. The segregation device is configured to prevent granules of fuel in solid form from passing between the reservoir and the combustion chamber. The segregation device includes orifices to allow the passage of the fuel, once the fuel has become pasty, liquid or vaporized.

Abstract: A cooling device for regulating the temperature of a heat source of a satellite. The cooling device comprises at least one fluid loop is formed by an evaporator comprising a tank, at least one condenser, two conduits connecting the evaporator to the condenser, a heat transfer fluid flowing inside the fluid loop. The cooling device further comprises a device for pressurizing the fluid loop or a thermal damper. The thermal damper comprises a variable volume leak-tight chamber having a volume which varies on the basis of the operating temperature of the fluid loop so as to provide a substantially constant temperature inside the fluid loop.

Abstract: A device for cooling at least two distinct heat sources comprises a closed circuit in which a diphasic fluid flows. At least one capillary evaporator is configured to be placed in thermo contact with one of the heat sources, referred to as the primary heat source. Each other heat source referred to as a secondary heat source that is to be cooled. At least one exchanger configured to be placed in thermal contact with the secondary heat source. At least one first condenser positioned downstream of the evaporator, and upstream of the at least one exchanger. At least one last condenser positioned upstream of the evaporator and downstream of the at least one exchanger.

Abstract: Each loop of the device includes an evaporator and a condenser connected by an outer tube in a portion of which extends a thermally insulating sleeve having one end that can lead into the condenser and another end that surrounds a first portion (8a) of a microporous mass provided in the outer tube and pumping by capillarity a liquid-phase heat-carrier fluid flowing in the insulating sleeve of the condenser towards the evaporator, while the gaseous-phase fluid flows from a vapor-collecting central duct in a second portion of the mass of the evaporator towards the condenser in a duct inside said outer tube. The invention can be used for the thermal energy transfer from an electronic component or circuit defining a heat source in relation with the evaporator to a cold source in relation with the condenser.

Abstract: The invention relates to a heat transfer system comprising one main capillary pumped diphasic fluid loop and a secondary capillary pumped diphasic fluid loop suitable for cooling at least one hot source. The main fluid loop and the secondary fluid loop comprising one evaporator, a vapour pipe capable of conveying the cooling fluid in the vapour state from the evaporator to a condenser, a condenser and a liquid pipe capable of conveying the cooling fluid in the liquid state from the condenser to the evaporator so that the cooling fluid of the main fluid loop is in heat exchange with the cooling fluid of the secondary fluid loop.

Abstract: The thermal control device comprises at least one network of capillary heat pipes, in which each heat pipe comprises a tube enclosing an essentially annular longitudinal capillary structure, for the circulation of a two-phase heat-transfer fluid in the liquid phase, and surrounding a central channel for the circulation of said two-phase fluid in the vapor phase. The tubes of at least two heat pipes of the network intersect and are interconnected in such a way that at each intersection of heat pipes forming a node of the network, an exchange of fluid in the liquid phase can take place by capillary action between the capillary structures of said two or more heat pipes, and such that, simultaneously, an exchange of fluid in the vapor phase can take place by free circulation between the central channels of said two or more heat pipes.

Abstract: Each loop of the device includes an evaporator and a condenser connected by an outer tube in a portion of which extends a thermally insulating sleeve having one end that can lead into the condenser and another end that surrounds a first portion (8a) of a microporous mass provided in the outer tube and pumping by capillarity a liquid-phase heat-carrier fluid flowing in the insulating sleeve of the condenser towards the evaporator, while the gaseous-phase fluid flows from a vapour-collecting central duct in a second portion of the mass of the evaporator towards the condenser in a duct inside said outer tube. The invention can be used for the thermal energy transfer from an electronic component or circuit defining a heat source in relation with the evaporator to a cold source in relation with the condenser.

Abstract: The device includes an evaporator and a condenser connected by an outer tube in which extends at least one inner tube having one end leading into the condenser and another end connected to an end of a central duct for collecting the vapours of a heat-carrier fluid, in a microporous mass provided in the outer tube and pumping by capillarity the liquid-phase fluid flowing in at least one outer duct between the outer and inner tubes from the condenser to the evaporator, while the vapour-phase fluid flows from the evaporator to the condenser in at least one inner duct inside said at least one inner tube. The invention can be used for the thermal energy transfer from an electronic component or circuit in relation with the evaporator to a cold source in relation with the condenser.

Abstract: The thermal control device comprises at least one capillary pumped diphasic fluid loop, comprising, in a known manner, an evaporator extracting the heat from a so-called hot source and connected via a vapour pipe to a condenser in which the condensation of the fluid vapour releases thermal energy transmitted to a so-called cold source, the condenser being connected via a liquid pipe to the evaporator, and the device moreover comprises at least one thermal capacitor in permanent heat exchange relationship with liquid phase fluid in said at least one diphasic fluid loop. Use in particular with space vehicles such as satellites.