SOLID PROPELLANT ROCKET ENGINE Russian patent published in 1999 - IPC

Abstract RU 2135812 C1

FIELD: aircraft engineering; rocket manufacturing. SUBSTANCE: engine has nozzle diaphragm formed by set of equidistant thin-walled cups with flange made of foil. Height of cup flange is equal to value protected by invention. Longitudinal zigzag corrugations are uniformly spaced over circumference of cup flange and antiadhesion layers are placed between cup bottoms. Design of engine provides reliable division of diaphragm into small mass parts of high sailing capacity. EFFECT: provision of safe starting of rockets from aircraft guides. 2 dwg

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RU 2 135 812 C1

Authors

Surnachev A.F.

Sokolov G.F.

Morozov V.D.

Filimonov G.D.

Makhonin V.V.

Dates

1999-08-27—Published

1997-11-25—Filed