旋 转 对 固 体 火 箭 发 动 机 两 相 流 点 火过 程 影 响 仿 真 研 究

In order to study the influence law of high-speed spin on condensed phase ignition transient process of solid rocket motor with internal and external burning tubular propellants，the ignition model of solid rocket motor was established by the user defined function（UDF）of computational fluid dynamics（CFD）software，and the ignition process of condensed phase was simulated under the condition of spin. The correctness of the numerical model was verified by comparing the numerical results with the interior ballistics ground spin test results. The results showed that：（1）a large number of particles gathered at the front end of the combustion chamber due to the centrifugal motion of igniter gas particles，and some particles adhered to the solid rocket motor wall for a long time.（2）The particle ratio increased from 20% to 40%，and the ignition pressure peak decreased by 3. 93%. The increase of solid rocket motor spin speed could lead to the increase of internal ballistic equilibrium pressure，but the ignition pressure peak gradually decreased， and the appearance time of pressure peak was delayed. When the spin speed reaching 15 000 r/min， the ignition pressure peak disappeared.（3）With the increase of spin speed， the heat transfer between ignition particles and propellant increased， the flame - spread period decreased， but the chamber-filling period and ignition delay increased. Compared with static condi⁃ tion the ignition delay increased by 23. 76% at 15 000 r/min when the particle ratio was 20%.