SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2004 - IPC

FIELD: rocket engines. SUBSTANCE: proposed solid-propellant rocket engine contains combustion chamber with cylindrical section, front and rear bottoms, propellant charge consisting of two parts and connected with combustion chamber, and nozzle with heat-protective coating and recesses part located sufficiently close to surface of charge. Charge is divided into two parts by flexible diaphragm installed near recesses part of nozzle. Part of charge located between front bottom and flexible diaphragm is made of fuel featuring high combustion temperature. Part of charge between rear bottom and flexible diaphragm is made of fuel with low combustion temperature and it has at least one groove near flexible diaphragm. Recessed part of nozzle, surface of charge with low combustion temperature and rear bottom form annular channel whose flow section area changes continuously from rear bottom to head point of recessed of nozzle. EFFECT: provision of rocket engine featuring high combustion temperature with reduced passive mass of construction owing to reduction of mass of thermal protection. 2 cl, 1 dwg