The invention relates to a control system of a hovercraft comprising one engine and one propulsion fan (1) enclosed in a duct (2) in which swivel side flaps (3) are located, said control system being characterized in that downstream the duct (2) there are ...

The invention relates to a rocket engine with the multi-stage combustion of a mixture of propellants, having at least one pre-combustion chamber and a main combustion chamber, a propellant mixture supply system to these chambers, including a fuel and oxida...

The subject of the invention is a solid rocket propellant grain comprising frontal surfaces and a lateral surface, characterised in that it comprises a first type layer which is completely filled in cross-section with a solid propellant material with an in...