An injector element (1) of coaxial design is provided for a rocket drive for operation with a first and a second propellant, comprising a central body (5), a sleeve (2) and a flow splitter (7). The central body (5) comprises a flow channel with an outlet, ...

An injector element (1) of coaxial design is provided for a rocket drive for operation with a first and a second propellant, comprising a central body (5), a sleeve (2) and a flow splitter (7). The central body (5) comprises a flow channel with an outlet, ...

An injector (22) includes an injector body (40) that has at least an injection side surface (32). A plurality of passages (50) extends within the injector body (40) for injecting combustion fluids at the injection side surface (32). The plurality of passag...

A rocket engine (20) includes a generally cylindrical annular combustion chamber (22), an injector (38) attached to an injector end (34) of the combustion chamber (22), a generally cylindrical annular step collar (46) fitting within the combustion chamber ...

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...

The invention relates to power plants, in particular to devices for mixing and atomizing propellant components, and may be used for development injection elements and injector heads of liquid-fuel rocket engines (LRE). The task of the invention is to incre...

The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A pro...