Abstract: A space propulsion module for fitting to spacecraft is provided. The space propulsion module includes a solid propellant chemical thruster including a main body, and at least one electric thruster. The at least one electric thruster is mounted on main body of the solid propellant chemical thruster.

Abstract: A method of generating electricity with a fuel cell includes a phase in which the cell is primed; and a phase in which the cell functions at a stable rate, during which the cell, fed with a hydrogenated gas, generates electricity and heat. In order to prime the cell, it is fed with a hydrogenated gas including at least 70 vol. % hydrogen, generated by self-sustaining combustion of at least one hydrogenated gas-generating solid pyrotechnic charge; and while it is operating at a stable rate, the cell is fed with a hydrogenated gas containing at least 85 vol. % hydrogen, generated by thermal decomposition of at least one hydrogenated gas-generating solid pyrotechnic charge; a portion of the heat produced by the operating cell being transferred to the at least one solid charge in order to start and maintain the thermal decomposition thereof.

Abstract: An emergency start system for a turbine engine of an aircraft including at least one solid propellant gas generator, an electrically controlled ignition device, a computer connected to the ignition device, and at least one starter motor comprising a turbine for driving a shaft which is for coupling to a shaft of the turbine engine The outlet of the gases from the generator are connected to the inlet of the turbine of the starter motor.

Abstract: A method of generating electricity with a fuel cell includes a phase in which the cell is primed; and a phase in which the cell functions at a stable rate, during which the cell, fed with a hydrogenated gas, generates electricity and heat. In order to prime the cell, it is fed with a hydrogenated gas including at least 70 vol. % hydrogen, generated by self-sustaining combustion of at least one hydrogenated gas-generating solid pyrotechnic charge; and while it is operating at a stable rate, the cell is fed with a hydrogenated gas containing at least 85 vol. % hydrogen, generated by thermal decomposition of at least one hydrogenated gas-generating solid pyrotechnic charge; a portion of the heat produced by the operating cell being transferred to the at least one solid charge in order to start and maintain the thermal decomposition thereof.

Abstract: A pyrotechnic process for providing very high purity hydrogen, includes the combustion of at least one solid pyrotechnic charge capable of generating hydrogen-containing gas for the production of a pressurized hot hydrogen-containing gas that contains at least 70% by volume of hydrogen; and the purification of at least one portion of the pressurized hydrogen-containing gas, by passing through a metallic hydrogen separation membrane maintained at a temperature above 250° C., in order to obtain, at the outlet of the membrane, a hydrogen-containing gas that contains at least 99.99% by volume of hydrogen.

Abstract: The invention relates to an emergency start system (20) for a turbine engine of an aircraft, characterised in that it comprises at least one solid-propellant gas generator (22), an electrically controlled ignition device (24), a computer (28) connected to the ignition device, and at least one starter motor (18) comprising a turbine (38) for driving a shaft (34) intended for being coupled to a shaft (54) of the turbine engine, the outlet of the gases from the generator being connected to the inlet (44) of the turbine of the starter motor.

Abstract: A space propulsion module in particular for fitting to spacecraft such as satellites, probes, or indeed the upper stages of rockets. According to the invention, the space propulsion module comprises a solid propellant chemical thruster (10) having a main body (11), and at least one electric thruster (30), said at least one electric thruster (30) being mounted on said main body (11) of the solid propellant chemical thruster (10).

Abstract: The present invention relates to a process for the self-regulated production as a function of the demand, under submerged conditions, of a gas (G), said gas (G) being generated by a chemical reaction between a liquid (L) and a solid (S) (hydrogen generated by hydrolysis of a metal hydride, for example) and not being polluted between the generation thereof and the delivery thereof. The present invention also relates to a device suitable for the implementation of said process.

Abstract: A pyrotechnic process for providing very high purity hydrogen, includes the combustion of at least one solid pyrotechnic charge capable of generating hydrogen-containing gas for the production of a pressurized hot hydrogen-containing gas that contains at least 70% by volume of hydrogen; and the purification of at least one portion of the pressurized hydrogen-containing gas, by passing through a metallic hydrogen separation membrane maintained at a temperature above 250° C., in order to obtain, at the outlet of the membrane, a hydrogen-containing gas that contains at least 99.99% by volume of hydrogen.

Abstract: The invention relates to an electricity production system for feeding electrical energy to a device of an aircraft. The system comprises a generator for generating gaseous hydrogen from hydrogen in non-gaseous form, a main tank connected upstream to the generator and for containing gaseous hydrogen under a pressure substantially higher than atmospheric pressure, the gaseous hydrogen being produced by the generator, at least one fuel cell, an expander connected upstream to the main tank and downstream to the fuel cell(s), where upstream and downstream are defined relative to the flow direction of the hydrogen under normal conditions of operation of the system, and a control device that regulates the flow rate and the pressure of the gaseous hydrogen from the main tank to the fuel cell(s) via the expander.

Abstract: The present invention relates to a process for the self-regulated production as a function of the demand, under submerged conditions, of a gas (G), said gas (G) being generated by a chemical reaction between a liquid (L) and a solid (S) (hydrogen generated by hydrolysis of a metal hydride, for example) and not being polluted between the generation thereof and the delivery thereof. The present invention also relates to a device suitable for the implementation of said process.

Abstract: The main subject of the present invention are solid compounds capable of generating hydrogen by a self-sustaining combustion reaction. Their composition comprises borazane and/or polyaminoborane and at least one inorganic oxidant, advantageously chosen from ammonium nitrate, alkali metal nitrates, alkaline-earth metal nitrates, metal nitrates, metal oxides, oxidants of the family of dinitramines and mixtures thereof. It also relates to the generation of hydrogen by self-sustaining combustion of at least one such compound.

Abstract: The invention relates to a method and to an autonomous device (10d) for injecting a fluid (F), that uses pyrotechnical means (1d). The invention can be used in particular for injecting a protection fluid (F) into a system that is subject to overheating (8d). The method is characterized in that it uses a thermally triggered charge (1d).

Abstract: One subject of the present invention is a propulsion method comprising: the injection, into at least one combustion chamber (1), of at least one liquid oxidizer (OX) and of hydrogen (H2); the combustion of said at least one liquid oxidizer (OX) and hydrogen (H2), in said at least one combustion chamber (1), for the generation of combustion gases; and expulsion of said combustion gases. Said process comprises, upstream of said injection: the generation of at least one portion of said hydrogen (H2), advantageously of all said hydrogen (H2), from at least one solid compound (5?); said generation from said at least one solid compound (5?) comprising a combustion reaction between said at least one solid compound (5?) chosen from alkali metal borohydrides, alkaline-earth metal borohydrides, borazane, polyaminoboranes and mixtures thereof and an oxidizing charge (5?). Another subject of the present invention is a propulsion device suitable for the implementation of said method.

Abstract: The main subject of the present invention are solid compounds capable of generating hydrogen by a self-sustaining combustion reaction. Their composition comprises borazane and/or polyaminoborane and at least one inorganic oxidant, advantageously chosen from ammonium nitrate, alkali metal nitrates, alkaline-earth metal nitrates, metal nitrates, metal oxides, oxidants of the family of dinitramines and mixtures thereof. It also relates to the generation of hydrogen by self-sustaining combustion of at least one such compound.

Abstract: The invention relates to a method and to an autonomous device (10d) for injecting a fluid (F), that uses pyrotechnical means (1d). The invention can be used in particular for injecting a protection fluid (F) into a system that is subject to overheating (8d). The method is characterised in that it uses a thermally triggered charge (1d).