摘要
通过同心筒发射装置燃气排导的流场分析,提出了同心筒气体动力学过程的简化模型,分析了燃气从发动机喷管流出后分别经历一个的变截面和摩擦管流的过程,并对一个具体的同心筒发射装置的流场进行了数值模拟,验证了所提出的简化气体动力学原理模型的正确性.然后根据原理分析,总结出了几个同心筒结构优化设计中需要考虑的参数,解释了这些设计参数的作用原理,使同心筒的优化设计有了初步的理论指导和优化方向,并根据基本原理给出了一种快速估算最小狭缝宽度和平均附加弹射力的方法.
The simplified model of concentric canister launcher （CCL） was proposed ac- cording to the gas flowing and exhausting process. The gas from the rocket motor nozzle flows through a stage of reducing cross-area and experiences a uniform section frictional pipe flow. A numerical simulation of a certain CCL case was conducted to verify that the simpli- fied theory model was reasonable. Then some structural factors of optimizing design of CCL were summarized and explained how these factors worked from the analysis of the simplified theory model. According to the basic simplified theory model, a convenient and simple method to estimate the smallest size of gap and the additional eject force of missile has been given. And the simplified theory model also can be used to guide and improve the design of CCL.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2012年第3期501-507,共7页
Journal of Aerospace Power
基金
国家自然科学基金(10702009)
飞行器动力学与控制教育部重点实验室开放基金(GFTD0803)
关键词
同心筒
燃气射流
数值模拟
气体动力学原理
设计参数
CCL （concentric canister launcher）
gas jet
numerical simulation
aerodynamic theory
design parameters
