FIELD: rocketry; control of thrust in value and direction. SUBSTANCE: engine has fixed part 2 and movable frame 3 engaging with fixed part over spherical belt, and bell 4 with control surface serves 10. Bell is arranged on movable frame for turning around longitudinal axis and for longitudinal displacement. It is coupled with movable frame by system of obliquely directed rods 5 forming hyperboloid of revolution of one nappe composing the end of through flow part of nozzle unit. Cooling gas generator (or sublimating component 7) is arranged in toroidal space 6 formed by movable frame and hyperboloid of revolution of one nappe. Widening part of hyperboloid of revolution of one nappe is closed by cup 9 at side of space 6. EFFECT: simplified design, improved reliability, reduced weight and enlarged operating capabilities. 3 cl, 7 dwg
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