FIELD: rocket engines.
SUBSTANCE: invention relates to rocket engines, in which for thrust vector control in flight there used are various controls located at the nozzle edge. Chamber of high-altitude liquid-propellant engine (LPE) with peripheral rudders on the nozzle edge contains a supersonic part of the nozzle with exhaust vanes installed in hinges at the nozzle edge, a rotary mechanism and a control actuator. Exhaust vanes feature variable-length thickness with stiffness ribs arranged on outer surface and bracket for connection of vane with control actuator. Rotary mechanism comprises link with lug pivotally connected to control actuator and bracket fixed on stiffness rings made on nozzle part of chamber, spring bringing link with lug into working position, in which it is fixed in working position retainer located on bracket.
EFFECT: described is a chamber of a high-altitude liquid-propellant engine with exhaust vanes at the nozzle edge.
1 cl, 6 dwg
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