HIGH-SENSITIVITY IMPACT TYPE INITIATOR DESIGN FOR IGNITION OF POWDER CHARGE IN ROCKET ENGINES Russian patent published in 2025 - IPC F42C19/10 

FIELD: aviation; cosmonautics.

SUBSTANCE: invention relates to ignition means, mainly for ignition of powder charges in catapult seats, ballistic missile engines and objects of similar design in space-rocket equipment. Impact-type initiator for ignition of powder charge in rocket engines comprises cylindrical shell accommodating anvil resting on capsule composed by cap with impact-ignition composition. Said anvil has vertical cylindrical wall extending in both directions relative to taper anvil to make two chambers communicated via ignition holes. In the lower chamber formed by the anvil and the bottom of the cover there is a capsule, and in the upper chamber formed by the anvil and the rolled edges of the cover, and in the ignition holes, there is an intensifying ignition charge. Ratio of the area of the outer surface of the bottom of the cap to the area of the outer surface of the bottom of the shell is equal to 0.48. Ratio of volume occupied by intensifying primer charge to total volume of anvil top chamber varies from 0.15 to 0.55. Ratio of the diameter of the bottom of the shell and the rolled part is equal to 1, and the ratio of the inner diameter of the cap to the diameter of the working part of the conical anvil is equal to 4.6. Cap contains impact-ignition composition consisting of lead trinitroresorcinate with boron, potassium chlorate, tetrazene, antimonium with their certain weight ratio.

EFFECT: maintaining reliability of ignition at increase of thermal stability, sensitivity to an impact pulse provided that the required dimension corresponding to a seat is maintained.

1 cl, 2 dwg, 3 tbl