期刊论文

Solid propellant grain motion under lateral acceleration

中文

固体火箭技术

Journal of Solid Rocket Technology

1006-2793

2016

39

1

23-27

10.7673/j.issn.1006-2793.2016.01.004

上海航天科技创新基金(SAST201247)； 上海航天技术研究院-上海交大航天先进技术联合研究中心资助项目(USCAST2013-31)；

本校为其他机构

采用Greatrix燃速增大模型计算燃面上各点瞬时燃速,运用Fluent局部网格重构技术,通过UDF函数实现控制环形燃烧室的非均匀推移过程,对6种横向加速度条件下HTPB推进剂燃速特性进行了数值模拟计算,与文献实验结果的相对误差为8.2%。结果分析表明,最大燃速出现在加速度与燃面垂直位置上,且随加速度增大而增大,50g加速度下的最大燃速比基础燃速提高82.5%;燃面上各位置燃速和加速度敏感系数均随载荷方位角的增大而减小;引入加速度敏感系数修正因子,建立了随加速度和载荷方位角同时变化的燃速公式。上述结论可为固体火箭非对称药柱设计提供参考依据。

Numerical simulation model of HTPB propellant combustion was established under the condition of six different lateral accelerations by calculating the transient combustion rate based on the Greatrix algorithm. Non-uniform motion of annular combustion chamber was presented by Fluent local re-mesh method. Compared with the experimental results of the literature, the relative error is 8.2%. The simulation results shows that the maximum combustion rate increases along with acceleration and appears on the position where acceleration vector and grain...