SOLID PROPELLANT ROCKET ENGINE Russian patent published in 2010 - IPC F02K9/18 

FIELD: engines and pumps.

SUBSTANCE: invention is related to the field of rocket engineering, namely to solid propellant rocket engines and charges of solid propellant rocket engines of various purpose. Solid propellant rocket engine comprises body, front and nozzle bottoms, charge of solid propellant with slots, arch of which increases towards nozzle bottom of engine. Charge is made of three serially arranged sections: at the first and second sections thickness of burning arch increases, the third section is arranged with permanent thickness of burning arch. Values of burning arch thicknesses at each of sections are defined by ratios that are defended by the present invention. At the second and third sections there are slots arranged with triangular and rectangular profiles, which are combined into two symmetrically arranged groups with even location of slots in each of groups. Ratio of angles between slots of rectangular and triangular profiles makes 0.2…0.5. Height of rectangular profile slots makes 0.1…0.3 of required thickness of burning arch. Angle of incline of triangular profile slots tops to axis of engine makes 30…60°.

EFFECT: invention makes it possible to increase volume filling of engine chamber with fuel, to provide for increased level of traction at initial stage of engine operation, to reduce degressive burning down sections of fuel, and also to reduce gradient of traction growth as engine reaches mode.

3 cl, 3 dwg