The secondary
gunpowder starter comprises a main shell and a spray
pipe seat, the main shell and the spray
pipe seat are connected through a
flange structure, and a
combustion chamber is formed in the main shell and the spray
pipe seat; the
flange structure comprises a first
flange arranged on the end face of the main shell and a second flange arranged on the end face of the spray pipe base, and the first flange and the second flange are fixed through fastening bolts. The increase of the
internal temperature of the
gunpowder starter is controlled through the
modes that water in the annular cavity of the spray pipe seat is vaporized to take away heat and radiative
heat transfer is carried out between the main shell and the flange structure of the spray pipe seat. The technical problem that high-temperature and high-pressure
fuel gas cannot be isolated, so that a secondary
gunpowder starter burns earlier than a preset time in the first starting and working process of a liquid
rocket engine is solved, and the technical problems that in an existing secondary starting gunpowder starter, a heat insulation structure is complex in manufacturing and mounting process, the falling probability is high, and the service life is long are solved. And the starter is high in cost and low in reliability.