二次燃烧对自力弹射内弹道影响分析
The Impact of Afterburning on Internal Ballistic of Self-Ejection
蒲鹏宇 1穆洪斌 1何定洲 1马保海 2宁雷1
作者信息
- 1. 北京宇航系统工程研究所,北京 100076
- 2. 中国运载火箭技术研究院,北京 100076
- 折叠
摘要
目前弹射所用低温药柱的燃烧平衡产物中含有可燃气体成分,遇初容室内氧气后发生二次燃烧,影响初容室内流场与弹射内弹道特性.为了分析二次燃烧对自力弹射方案内弹道的影响,建立了自力弹射可压缩流动仿真模型,结合有限速率化学反应模型与动网格技术,利用PISO(压力隐式算子分裂法)算法对控制方程进行数值求解.计算结果表明,二次燃烧使得初容室初始压力峰值时刻提前,并影响初始压力峰值大小.仿真分析结果为自力弹射内弹道设计提供了理论参考.
Abstract
The combustion equilibrium species of low-temperature propellant used in launches con-sist of some unburned gases.These gases generate afterburning when mixed with the oxygen in the initial vessel.The afterburning influences the internal flow and the performance of internal ballistic.To analyze the impact of afterburning,a compressible flow modelis established combined with finite rate chemistry and dynamic mesh to simulate the self-ejection process and the PISO al-gorithm is used to solve the conservative equations.The results show that the afterburning brings forward the first peak of pressure in the initial vessel and affects the peak value.The analysis pro-vides a theoretical reference for the internal ballistic design of self-ejection.
关键词
二次燃烧/弹射内弹道/自力弹射Key words
Afterburning/Internal ballistic of ejection/Self-ejection引用本文复制引用
基金项目
国家自然科学基金青年基金(5190061543)
出版年
2024
NETL
NSTL
万方数据