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

作　　者：吴秀玲[1] 梁增友[1] 周海清[2] 周俊祥[2] 

机构地区：[1]华北工学院,山西太原030051 [2]北京理工大学,北京100081

出　　处：《弹箭与制导学报》2003年第3期48-49,共2页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：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.

关 键 词：复合增程弹 火箭发动机 闭气装置 闭气性能 解脱性能 

分 类 号：TJ413.4[兵器科学与技术—火炮、自动武器与弹药工程]