固体火箭发动机撞击靶板安全性数值分析

Numerical analysis for safety of solid rocket motor impacting target

为研究固体火箭发动机撞击安全性，建立了固体火箭发动机撞击靶板的计算模型，模型中发动机的推进剂装药采用点火增长反应速率方程。采用非线性有限元流体动力学方法，对发动机径向撞击靶板过程进行了数值模拟，分析了不同撞击速度下发动机中推进剂装药的反应情况。计算结果表明，发动机径向撞击靶板爆炸的临界速度范围为150～200m／s；低强度多次撞击过程中推进剂会发生延迟爆轰情况。

In order to investigate the impacted safety of solid rocket motor, the calculation models for simulating the solid rocket motor impacting on the target were created. In the models, the ignition and growth of reaction rate equation was adopted to prescribe the initiation and detonation process of propellant. The process of the solid rocket motor on radial impact was numerically simulated by the nonlinear finite element hydrodynamics algorithm. The reaction states of propellant under different impact speed were analyzed. The results show that the critical detonation speed of solid rocket motor impacting target along radial is from 150 m/s to 200 m/s. The delayed-detonation of propellant occurs during multiple impacting by low strength.