SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 1999 - IPC

FIELD: construction of sustainer stages. SUBSTANCE: engine has casing with end plates, charge fastened with casing and provided with blind central passage. Charge is divided by combustible partition into two parts. Combustible partition is made in form of curvilinear surface with central hole symmetrical relative to longitudinal axis of engine. Cross-section area of partition decreases in way of rear end plate; front portion of charge and partition are fastened with front end plate. It is preferable to make partitions in form of truncated cone. Proposed engine may be used for high aspect ratio and low aspect ratio. EFFECT: enhanced efficiency of rocket engine due to reduction of stressed deformed state of charge in area of passage and in area of fastening the charge with casing; possibility of approaching engine charge-to-weight ratio to level of ratio of high stages. 2 cl, 4 dwg, 1 tbl