Gas generator of a rocket/ram jet motor

摘要

A gas generator of a rocket/ram jet motor for a non-spinning missile with a predominantly horizontal trajectory (flight path), in the form of a combustion chamber which encloses a solid propulsion charge which operates as an end burner, consisting of a combustion chamber casing having at least one horizontal plane of symmetry and one vertical plane of symmetry, of a front end wall which closes the combustion chamber casing at the front, and of a rear end wall which closes the combustion chamber casing at the rear, at an axial distance from the solid propulsion charge, having at least one gas outlet nozzle, which is symmetrical with respect to the vertical longitudinal centre plane, the centroid of the flow cross-sections of the gas outlet nozzle and the overall centroid of the flow cross-sections of the gas outlet nozzles lying at right angles underneath the axis of symmetry of the gas generator in a plane which is at right angles to the axis of symmetry of the gas generator and intersects the narrowest flow cross-section of the gas outlet nozzle or the narrowest flow cross-sections of the gas outlet nozzles in the region of the rear end wall.