سال انتشار: ۱۳۸۶

محل انتشار: دومین کنفرانس احتراق ایران

تعداد صفحات: ۱۰

نویسنده(ها):

Maneshian – Graduate student، Dept.of Mechanical Engineering,Shiraz University Molla-Sadra Ave.,Shiraz
Akbari – Assistant professor and corresponding author، Dept.of Mechanical Engineering,Shiraz University Molla-Sadra Ave.,Shiraz

چکیده:

The performance of a solid rocket motor depends heavily on the flow characteristics,the chemical composition of the grain,combustion products and the burning rate.In this study the start-up transient internal ballistics of a typical solid rocket motor (SRM)is numerically simulated.Two burning rate laws are used to model simple and erosive burning.Governing equations of 2 -dimensional inviscid flow are solved using an explicit MacCormack finite difference technique in which the locations of shock waves are captured by the solution scheme.Erosive burning increases the chamber pressure and thrust during the early portion of burning for a particular motor.