Wyniki wyszukiwania - BazTech

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Specific Design Features of Solid Propellant Rocket Motors for Shoulder-Launched Weapon Systems

Zecevic B., Terzic J., Baskarad M., Catovic A., Serdarevic-Kadic S., Pekic Z.

Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa

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2011

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Vol. 2, Nr 2 (4)

7-28

EN

Solid propellant rocket motors for Shoulder Launched Infantry Weapon Systems (SLWS) are characterized with a very short burning time, high-pressure combustion and a wide spectrum of design solutions for rocket motor structure. Interior ballistic behaviour of such rocket motors depends on many factors such as design structure, propellant grain shape, propellant grain joint to the rocket motor case, type and location of the igniter, spinning mode and nozzle design. Erosive burning also plays important role due to high combustion gases mass flow rate. Numerical simulation of the igniter combustion gases flow through the hollow of the propellant grain tubes with gas temperature distribution was carried out in this paper. Results confirmed assumptions that igniter interior gas flow affected duration of the pressure rise. A mathematical model approach for prediction of the curve p = f(t) which was included in a model of the corrected propellant grain burning surface for two types of short-time rocket motors has been presented. A good agreement with measured curves was achieved.

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Prediction of Internal Ballistic Parameters of Solid Propellant Rocket Motors

Terzic J., Zecevic B., Baskarad M., Catovic A., Serdarevic-Kadic S.

Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa

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2011

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Vol. 2, Nr 4 (6)

7-26

EN

A modular computer program named SPPMEF has been developed which isintended for purposes of predicting internal ballistic performances of solid propellantrocket motors. The program consists of the following modules: TCPSP (Calculation of thermo-chemical properties of solid propellants), NOZZLE (Dimensioning of nozzle and estimation of losses in rocket motors), GEOM (This module consists of two parts: a part for dimensioning of the propellant grain and a part for regression of burning surface) and ROCKET (This module provides prediction of an average delivered performance, as well as mass flow, pressure, thrust and impulse as functions of burning time). The program is verified with experimental results obtained from standard ballistic rocket test motors and experimental rocket motors. Analysis of results has shown that the established model enables high accuracy in prediction of solid propellant rocket motors features in cases where influence of combustion gases flow on burning rate is not significant.

3

Comparison of Lethal Zone Characteristics of Several Natural Fragmenting Warheads

Zecevic B., Catovic A., Terzic J.

Central European Journal of Energetic Materials

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2008

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Vol. 5, nr 2

67-81

EN

Research of HE warheads lethal zone is very complex topic because of large number of controlled and independent, sometimes correlated, influencing factors. Capability for prediction of lethal zone is based on complexity of databases regarding natural fragmentation parameters, which should contain data about warhead body material characteristics, types of explosive charge, number, mass, initial velocity and spatial distribution of fragments, battlefield terrain, distribution of soldiers on battlefield, etc. Based on experimental research (fragmentation test in Arena facilities with two types of artillery projectiles and two types of rocket warheads), analytical and numerical methods used - projectiles lethal zones are predicted and analyzed. Influence of projectile design and explosive charges on warhead lethal zone is analyzed.