سال انتشار: ۱۳۸۶

محل انتشار: هفتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۷

نویسنده(ها):

Shafqat wahab – PhD student,Beijing University of Aeronautics & Astronautics, (BUAA), China
Xie Kan – PhD student, Beijing University of Aeronautics & Astronautics, (BUAA), China
Liu Yu – Professor, School of Astronautics, BUAA, 37 Xue Yuan, Road, Beijing 100083, China

چکیده:

This paper presents numerical investigation of two phase flow inside the nozzle and effect of two phases on the performance prediction of the Solid Rocket Motor Nozzle. The aluminum particles generate a two phase flow in the solid propellant combustion chamber. An Eulerian-Lagrangian description has been used to analyze the motion of the micrometer sized and discrete phase that consist of the larger particulates present in the Solid Rocket Motor. Uniform particles diameters and Rosin-Rammler diameter distribution method has been used for the simulation of different burning of aluminum droplets generating aluminum oxide smokes. The results obtained with the injected droplets size distribution shows the sensitivity of this distribution to the nozzle flow dynamics, primarily at the nozzle inlet and exit. The analysis also provides effect of two phases on performance prediction of Solid Rocket Motor.