SOLID PROPELLANT CHARGE Russian patent published in 2000 - IPC

Abstract RU 2145673 C1

FIELD: volley fire systems; rocket shells. SUBSTANCE: proposed charge has housing, protection-and- fastening layer, end face cups, head semicharge with star-like channel and tail semicharge with cylindrical channel. Charge is made with rounding off radii in places where cylindrical sections of star-like channel arms change into arm surface, being equal to 0.08-0.15 of thickness of head semicharge burning arch. Length of cantilever section of tail semicharge pointed to nozzle is equal to 0.6-1.5 of thickness of tail semicharge burning arch at beginning of cantilever section. Axisymmetrical recess converging in direction towards nozzle end face is made in area of front end face of tail semicharge. This recess includes the following conical sections arranged one after the other: maximum diameter section (Dmax) on front end face of tail semicharge equal to 1.2 - 1/5 of outer diameter of arms of head semicharge with taper angle of 25 - 35o and length of (0.015 - 0.03)L; section with taper angle of 3-8o and length of (0.02- 0.04)L; section with taper angle of 10-20o and length of (0.015-0.03)L, where L is length of tail semicharge. EFFECT: provision of solid propellant charge with 8-10% increase in volumetric fill factor at decrease in spread of output characteristics and reliability criteria in preset range of application. 3 dwg

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RU 2 145 673 C1

Authors

Semilet V.V.

Obozov L.I.

Peturkin D.M.

Filatov V.G.

Kashirkin A.A.

Aljazhedinov V.R.

Makarovets N.A.

Kuz'Mitskij G.Eh.

Fedchenko N.N.

Vinokurov Ju.A.

Grinberg S.I.

Talalaev A.P.

Kolesnikov V.I.

Amarantov G.N.

Kolach P.K.

Denezhkin G.A.

Nekrasov V.I.

Dates

2000-02-20Published

1999-05-25Filed