Rocket engine with two combustion chambers - has fuel mounted around secondary chamber with annular air intakes

摘要

The rocket has a nose (10) with the primary combustion chamber (12) at the front of the nozzle (11). The secondary combustion chamber (13) is located behind the nozzle. The combustion chambers are cylindrical. The chambers are mounted axially in the rocket. The ignition system (15) is in the primary combustion chamber. The rocket has an air intake diffuser (16) which surrounds the combustion chamber with air inlet passages (17). The fuel is mounted in a cylinder (18) around the secondary combustion chamber. Filters (21,22) are fitted between the combustion chambers.