ROCKET SOLID-PROPELLANT CHARGE

FIELD: self-propelled missiles. SUBSTANCE: solid-propellant charge can be used in engines of self-propelled missiles. Housing of charge is made conical, with diameter increasing towards rear end face and cylindrical section at rear end face. Channel of charge is made with cylindrical-conical undercu...

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Bibliographische Detailangaben
Hauptverfasser:	KUTSENKO G.V, AMARANTOV G.N, KORENNOJ A.V, SHVYKIN JU.S, KOLIKOV V.A, TALALAEV A.P, MAKAROV L.B, KUZ'MITSKIJ G.EH, PLOTNIKOVA T.N, VRONSKIJ N.M, FILIMONOV G.D, SURNACHEV A.F, KOLESNIKOV V.I, SHIPUNOV A.G, PICHKALEV ZH.A, SHATROVA EH.A, KOLACH P.K, FEDCHENKO N.N
Format:	Patent
Sprache:	eng
Schlagworte:	BLASTING COMBUSTION ENGINES HEATING HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS JET-PROPULSION PLANTS LIGHTING MECHANICAL ENGINEERING WEAPONS
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Beschreibung
Zusammenfassung:	FIELD: self-propelled missiles. SUBSTANCE: solid-propellant charge can be used in engines of self-propelled missiles. Housing of charge is made conical, with diameter increasing towards rear end face and cylindrical section at rear end face. Channel of charge is made with cylindrical-conical undercut at front end face terminating in cylindrical neck. Cylindrical section at end face is point3ed to nozzle with diameter larger than diameter of channel at front end face. Thickness of burning arch at end face pointed to nozzle is greater than thickness of burning arch at front end face. Radius front cup is strongly secured on housing. Rear cup is conical. Protective holding layer in place of connection of rear cup with housing is of increased thickness which decreases in direction of front end face. EFFECT: provision of integrity of charge at action of internal pressure and temperature deformations within wide temperature range. 2 dwg