Mechanism of composite propellant combustion at high acceleration

被引：0
|
作者：
Hassan, AH [1 ]
Ren, JX [1 ]
Liu, Y [1 ]
机构：
[1] Beijing Univ Aeronaut & Astronaut, Sch Astronaut, Beijing 100083, Peoples R China
来源：
THEORY AND PRACTICE OF ENERGETIC MATERIALS, VOL 5, PARTS A AND B | 2003年
关键词：
composite propellant; burning rate; acceleration; BDP model;
D O I：
暂无
中图分类号：
O414.1 [热力学];
学科分类号：
摘要：
An analytic model is developed to calculate the burning rate augmentation of metallized composite propellant in acceleration field based on BDP multiple flame model. The assumption that heat transfers from the hot particle to the burning surface uniformly is adopted. The behavior of the particles flying off the burning surface which may influence the burning rate is also considered. A calculation sample in the case of uniform flow field and results induced are given.
引用
收藏
页码：802 / 807
页数：6
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