SOLID PROPELLANT ROCKET CHARGE

FIELD: rocketry. SUBSTANCE: proposed solid propellant charge contains housing, end face cups, protective-and-fastening layer, star-like channel in bottom part of charge with cylindrical and conical sections. Initial thickness of burning arch in area of charge nozzle and face is 0.2-0.5 e1, bottom pa...

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Main Authors VINOKUROV JU.A, DENEZHKIN G.A, AMARANTOV G.N, KASHIRKIN A.A, TREGUBOV V.I, SEMILET V.V, SHUBKIN E.A, MAKAROV L.B, TALALAEV A.P, KOROLEVA N.B, KUZ'MITSKIJ G.EH, ROMANOVICH A.P, BOZH'JA-VOLJA N.S, KOLESNIKOV V.I, MAKAROVETS N.A, NEKRASOV V.I, PODCHUFAROV V.I, FEDCHENKO N.N, KOLACH P.K
Format Patent
LanguageEnglish
Published 27.12.2003
Edition7
Subjects
BLASTING
COMBUSTION ENGINES
HEATING
HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
JET-PROPULSION PLANTS
LIGHTING
MECHANICAL ENGINEERING
WEAPONS
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Summary:FIELD: rocketry. SUBSTANCE: proposed solid propellant charge contains housing, end face cups, protective-and-fastening layer, star-like channel in bottom part of charge with cylindrical and conical sections. Initial thickness of burning arch in area of charge nozzle and face is 0.2-0.5 e1, bottom part of charge is made with cantilever section of length equal to 0.6-1.8 e1 where e1 is mean in charge length initial thickness of burning arch. Distance between cross section of charge with at maximum ratio of burning surface to said section to area of through section o channel in said section and bottom end face of change is 0.8-0.9 L where L is length of charge. EFFECT: reliable functioning of charge made of high-energy high-elasticity propellants at simultaneous increase of specific loading density. 1 dwg
Bibliography:Application Number: RU20030109465