SOLID-PROPELLANT ROCKET ENGINE Russian patent published in 1997 - IPC

Abstract RU 2100635 C1

FIELD: rocketry; manufacture of solid-propellant engines with thrust cut-off. SUBSTANCE: solid-propellant engine includes body 1, nozzle 8, blank 18, igniter 19, charge 2 and hydraulic dampening unit consisting of sleeve 3 with differential piston 4 mounted for axial displacement, liquid cooler 7 located in under-piston chamber 5 of sleeve 3, sealing devices 14 and injection unit. Nozzle 8 is made in differential piston 4 of hydraulic dampening unit secured relative to sleeve 3 by means of pyrolock; tangential passages 15 provided over circumference of differential piston 4 are used to connect under-piston chamber 5 with above-piston chamber 6 of sleeve 3 in such way that above-piston chamber 6 of sleeve 3 performs function of centrifugal injector directed towards cavity of engine body 1; several guide members 17 are located at centrifugal injector outlet over circumference. EFFECT: enhanced efficiency. 3 dwg

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RU 2 100 635 C1

Authors

Ljanguzov S.V.

Dates

1997-12-27—Published

1995-06-28—Filed