Abstract: The invention concerns an electrothermal thruster (1) comprising a heating section (20) through which a propellant fluid (4) is intended to pass so that it is heated before it is exhausted, the heating section (20) being supplied by an electric power source (22). According to the invention, the electric power source (22) comprises photovoltaic cells (24) mounted on the heat exchanger (10) through which the propellant fluid (4) is intended to pass before it reaches the heating section (20). Application to the area of spacecraft propulsion.

Abstract: An electrothermal thruster including a heating section through which a propellant fluid is intended to pass to be heated before being exhausted, the heating section being supplied by an electric power source The electric power source includes photovoltaic cells mounted on the heat exchanger through which the propellant fluid is intended to pass before reaching the heating section. Such a device may, for example, find application in the area of spacecraft propulsion.

Abstract: The invention concerns a rocket engine wherein the combustion chamber includes at least one first monolithic component made of a thermostructural composite material comprising a porous wall through which the fuel is introduced in the core of the combustion chamber. A small part of the fuel is directed towards the neck for it to be cooled.

Abstract: The pointed end of a central spike, used in an engine of a space launcher, may have a deformable structure that can adopt either a folded position or a deployed position.

Abstract: The invention concerns a rocket engine wherein the combustion chamber consists of at least one first monolithic component made of a thermostructural composite material comprising a porous wall (5) through which the fuel is introduced in the core (C) of said combustion chamber. A small part of said fuel is directed towards the neck (3) for it to be cooled.

Abstract: The invention concerns a method for manufacturing a tank (1) for fluids under pressure comprising two compartments (8, 10).

Abstract: According to the present invention, the pointed end (11) of the central spike (7) consists of a deformable structure (13) that can adopt either a folded position or a deployed position.

Abstract: A solid propellant charge for a propulsion unit (1). The latter includes a casing (2) containing the solid propellant charge (3), in the form of an elongated body having a longitudinal axis (X--X), which charge (3) has, over part of its longitudinal extent, a propellant charge profile (4) of large combustion area and is subdivided, along the longitudinal axis (X--X), into at least two segments abutting one another with their respective mutually confronting faces. The propulsion unit furthermore includes a nozzle (5) and means (6) for igniting said charge. The propellant charge profile (4) of large combustion area is provided in that part of the propellant charge (3) which is intermediate along the longitudinal axis (X--X).

Abstract: A hot nozzle formed by a single unitary element formed of a three-dimensional weaving of a carbon substrate. This element is girdled by two thermal insulation rings--which provide suspension and orientation control for the nozzle. Application to nozzles for solid propellant propulsion units.