FIELD: engines and pumps.
SUBSTANCE: inventions refer to rocket engineering and can be used in thrust-zeroing and reverse-thrust solid-propellant rocket design, e.g. antitailspin rockets for aircraft testing. Said reverse-thrust rocket comprises a combustion chamber with coaxial and opposed jet nozzles, and a by-pass. The by-pass comprises a fixed sleeve with slots on the lateral surface, and a bushing axially advancing inside of the sleeve. The sleeve and the bushing are pinned, with each of them having two jimmers on the contact cylindrical surfaces one pair of which forms a hermetic cavity connected to a pyrocartridge cavity, while another pair surrounds the slots. The pin is mounted in the hermetic cavity, and its cross-section area is determined from the relation covered by the present invention.
EFFECT: invention allows ensuring reliable running of both forward- and reverse-thrust engine.
2 cl, 10 dwg
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