FIELD: engines and pumps.
SUBSTANCE: invention relates to aerospace engineering, particularly to nuclear rocket engines intended for long-term non-stop flights in atmosphere stratosphere and near earth space. Proposed engine comprises nuclear reactor, heat exchange chamber with radiation-protection bottom where through heat ducts are passed. Nuclear reactor heat exchange chamber represents a sectionalised design with heating channels separated by section walls and communicated by chambers to allow working body flow through all channels of all sections to supersonic nozzle or set of nozzles.
EFFECT: higher thrust-weight ratio and efficiency.
12 cl, 5 dwg
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