摘要
针对以往工程应用中认为导弹燃气易碎盖前盖由燃气直接冲破或导弹头部撞击破裂的情况,利用计算流体力学和试验方法对某导弹燃气易碎盖开盖过程进行了深入研究。结果表明,某导弹采用易碎前后盖技术,后易碎盖靠发动机喷管燃气冲开,前易碎盖靠发射时产生的扰动波打开;通过合理配置发射筒前后易碎盖开盖条件,能可靠保证发射筒盖的正常开启。
Aiming at the problems that the former friable lid of the missile was easy to be broken by gas or crashed by missile head in the engineering application, opening process of friable lid of one missile was deeply investigated by means of computational fluid mechanics and experimental method. The results show that the rear friable lid can be opened by nozzle gas, and the former friable lid can be opened by perturbation wave during the launch process when the missile applies the former and rear friable lid technique. Normal opening of the launch lid can be assured by reasonably allocating opening condition of the former and rear friable lid.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2007年第4期275-277,共3页
Journal of Solid Rocket Technology
关键词
易碎盖
燃气射流
计算流体力学
friable lid
gas jet
computational fluid mechanics
