The engine (1) for the propulsion of the upper stage of a space launcher has a longitudinal axis (L-L) and comprises a central core (7) and a functional lateral cone shaped surface (9) whose base (10) is located on the side of the engine. Pressurized gas f...

The combustion chamber (14) is delimited by an internal porous skin (17) and an external skin (18) forming an intermediate space between them. The fuel supplying the injectors (9) passes through the intermediate space. An exhaust pipe (16) channels the com...

The rocket motor combustion chamber (1) is constituted by a first monolithic thermo-structural composite material comprising a porous skin (5) through which a part of the fuel is introduced into the heart (C) of the combustion chamber. The combustion chamb...