固体火箭发动机冷气冲击过程数值分析

Numerical Analysis of Cold-Flow Impact Process of Solid Rocket Motor

使用工业氮气冲击固体火箭发动机药柱以模拟发动机点火瞬时产生的高压峰值对发动机壁面的压力冲击,分析模拟固体火箭发动机工作中的压力分布,对冷气冲击试验过程进行数值模拟;运用流体计算软件Fluent,对瞬时内流场进行二维轴对称非定常数值分析;研究分析结果表明:药柱头部位置受冲击力较大,容易产生结构完整性破坏,进一步验证发动机冷气冲击试验能够较好的模拟真实情况下发动机及药柱受到的影响,从而为发动机点火设计提供参考。

We used high pressure industrial nitrogen impact solid rocket motor to simulate the engine igni-tion when the high pressure peak of the grain and the impact of the engine surface,and measured the en-gine head,middle,end of pressure distribution,and simulated the process of solid rocket motor cold flow impact test. With the application of fluid calculation software fluent,we had numerical analysis within the instantaneous flow field in a two-dimensional symmetric unsteady. The results show the impact force is much stronger in the head of the propellant and it is easy to cause the damage of structural integrity. The results rein forced that the solid rocket motor cooling impact test is preferable to simulate the real pressure of engine and the effects of the propellant,which provides a powerful reference to designing and testing of the engine ignition.