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

FIELD: cut-off of spacecraft thrust by injection coolant into combustion chamber. SUBSTANCE: engine has case, nozzle, charge and hydraulic extinction unit which consists of sleeve with differential piston mounted in it for longitudinal motion. Piston is fixed relative to sleeve by means of locking device. Under-piston cavity of sleeve contains liquid coolant; under-piston and above-piston cavities of sleeves are communicated by means of helical passages which are provided on inner surface of sleeve and their section is varying in length. On side of shear of sleeve adjacent helical passages are combined over definite length forming continuous slot between differential piston and sleeve. Inner cylindrical surface of sleeve is provided with cylindrical band in immediate proximity of shear of sleeve. This band is provided with circular blank for sealing-up the above-piston cavity. EFFECT: enhanced efficiency and operational reliability due to increased depth of regulation of intensity of injection and passage area of injection unit at preset transversal sizes. 2 cl, 5 dwg