MILLING OF LARGE-SIZED FLEXIBLE OGIVAL SHELLS FOR LIQUID-PROPELLANT ROCKET ENGINE NOZZLES Russian patent published in 2014 - IPC B23Q3/14 B23C3/02 B21B31/00 

FIELD: process engineering.

SUBSTANCE: invention relates to rocketry and can be used for milling the grooves on outer surface of liquid-propellant rocket engine nozzle ogival shells and for withdrawal of said shells from the mandrel. Proposed method comprises fitting the ogival shell blank on the mandrel with outer surface profile equidistant to rocket engine nozzle ogival shell outer surface profile, milling the grooves on its outer surface and its withdrawal from the mandrel. Said mandrel consists of fixed part and moving part composed of stripper displacing upward by means of three pressure bolts thrusting against fixed part end at withdrawal of milled blank from the mandrel. Gypsum solution is used for provision of rigid joint between said mandrel and said ogival shell. To rule out the shell deformation the condition of dependence of adhesion between ogival shell and mandrel lateral surface and nozzle throat breaking point at the joint between the mandrel fixed and moving parts should be satisfied.

EFFECT: easy and mechanised withdrawal without shell deformation.

1 ex, 1 dwg