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New method of numerical simulation of combustion aluminium droplet in exhaust plume for SRM(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2010年06期
Page:
25-29
Research Field:
研究与设计
Publishing date:

Info

Title:
New method of numerical simulation of combustion aluminium droplet in exhaust plume for SRM
Author(s):
JIN Rui-bin;  XIANG Hong-jun
School of Astronautics, Beijing Univ. of Aeronautics and Astronautics, Beijing 100083, China
Keywords:
solid rocket motor;  exhaust plume;  aluminium particle;  combustion
PACS:
V435-34
DOI:
-
Abstract:
Multi-component chemical reaction models with finite rate are used to simulate the exhaust plume on the basis of summarization for the previous numerical simulation of the rocket jet. Lagrangian discrete phase model is used to simulate the particles composed of Al and Al2O3. The Al2O3 smoke velocity field is obtained with the fast Eulerian model. The gas phase, particulate phase, and smoke are coupled with source terms of mass, momentum and energy. The impact of aluminium particle combustion on the entire jet structure also can be simulated in order to accurately calculate the infrared radiation characteristics of the exhaust plume.

References:

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Memo

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Last Update: 1900-01-01