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2 Problemy Mechatroniki : uzbrojenie, lotnictwo, inżynieria bezpieczeństwa

2 2011

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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

2011

Vol. 2, Nr 2 (4)

7-28

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.

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

2011

Vol. 2, Nr 4 (6)

7-26

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.