FIELD: invention refers to rocket technique and may be used at creation of rocket engines on solid fuel.
SUBSTANCE: rocket propulsion plant on solid fuel has engines of previous and following stages with common bottom dividing their burning chambers, units of docking and separation of stages. Mouth of nozzle of engine of following stage is fulfilled in shape of turning lobes. Between common bottom and end-butt of charge of previous stage ring cavity is formed in which there are located unfolded to bottom lobes of mouth of nozzle and drive for their exposition. Units of docking and separation of stages are located in zone of output of ring cavity on cylindrical part of body of previous stage.
EFFECT: invention allows to ensure maximal filling with fuel engine of previous stage and also increases compactness of rocket propulsion plant and reduces its dimensions.
1 dwg
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