复合增程弹火箭发动机闭气装置及性能研究

The Study on Obturator of Rocket Engine for Compound Assisted Projectile

文中结合闭气装置工作环境,对火箭发动机的闭气装置性能进行了分析。利用所设计的试验装置对几种闭气装置的性能进行了测试。通过对测试结果的分析,确定了锥形塞与端盖相结合的闭气方式。该方式的闭气装置能够保证发射时对发动机可靠的闭气,在外弹道上发动机可靠点火和解脱。

In this paper obturator performance of rocket engine is analyzed according to work environment. Several obturator's performance is investigated by experiment. A cornplug combined endclosure pattern obturator is selected on the basis of experiment results. This pattern obsturator can satisfy requirement of rocket engine on the interior ballistic and exterior ballistic.