SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 1998 - IPC

FIELD: mechanical engineering; solid propellant rocket engines with controlled values of summary thrust pulse. SUBSTANCE: solid propellant rocket engine has housing 1, charge 2, cup 7 with service holes 8 made at angle to nozzle axis, summary through area of service holes being smaller than area of critical section 4 of nozzle, and shell 13 with stop lock 14. Bottom of cup of thrust control unit has through axial hole 9 accommodating central body 10 installed for axial displacement. Central body 10 is axially fixed relative to stationary part 3 of nozzle by stop cranks 11 fixed in radial direction by cup engaging with cranks. Telescopically shifted tip 6 of nozzle is provided with two-position detents in form of spring-loaded dowels 15 installed for radial displacement. Outer tilted (or conical) end faces of dowels get into mated sockets 16 on inner surface of shell. Inner end faces engage with outer side surface of stationary part of nozzle. Ring groove 17 is made in close vicinity to cut in outer side surface of nozzle stationary part. EFFECT: reduced perturbing action on rocket at operation of thrust control unit, improved reliability of engine and reduced overall dimensions. 2 dwg