Abrégé

A gasification chamber of a rocket engine for a solid propellant charge, the charge consists of a shell that is made of a solid polymeric propellant and a solid oxidizer that is arranged within a volume. An inner surface of the chamber is in a contact with a divided propellant charge and is equipped with injectors for the propellant and injectors for the oxidizer which are mounted in zones of contact with the propellant and the oxidizer respectively, and channels which combine flows of uniform components of the propellant charge. The gasification chamber is further equipped with a divider of the solid polymeric propellant and the solid oxidizer, the divider is arranged at an input of the gasification chamber and is made as a cylindrical shell, the shell has one pointed end face that is arranged between the solid polymeric propellant and the solid oxidizer of the divided propellant charge and another end face that rests on the inner surface of the gasification chamber.

Classes IPC  ?

• F02K 9/12 - Forme ou structure des charges de propergols solides composées d'au moins deux parties brûlant à des vitesses différentes
• F02K 9/32 - Parties de leur structureDétails non prévus ailleurs
• F02K 9/34 - CartersChambres de combustionLeurs chemises