SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 2000 - IPC

FIELD: rocket engineering. SUBSTANCE: engine has housing with bottom and free space at bottom, solid propellant charge connected to housing with axial channel, nozzle unit with inlet and outlet cones, insert installed in critical section of nozzle unit, ignition unit and nozzle cover. Channel in charge is made successively star-like, cylindrical and conical. Inner surface of nozzle unit inlet cone is made in form of three conical smoothly conjugated surfaces. Ignition unit is cantilever mounted on nozzle cover. Sizes of free space at bottom and free space of inlet cone, lengths of cylindrical and conical sections, section areas of star-like, cylindrical and conical sections, lengths of conical sections of inlet cone of nozzle unit at change end at insert, and radii of conjugation of inlet cone sections, and angles of tilting of these conical sections to longitudinal axis are protected by invention. Insert is made of fire spreading material with degree of spreading equal to 0.07-0.10 of critical section area, distance between critical section and front end face of igniter and area of ring section in plane of this end face between igniter outer diameter and inner surface of inlet cone being 0.15-0.65 of diameter of critical section and not less than 0.25 of its area, respectively. EFFECT: increased power characteristics of engine at the same overall dimensions, 15-20% increase in firing range. 3 dwg