摘要
为了更好地改善同心筒导弹垂直发射装置工作时导弹所面临的热环境,分析了影响筒口处燃气温度的因素和出口燃气温度降低过程中的气体动力学原理,并首次从能量守恒的角度分析了以前科研人员在降低出口燃气温度方面所做的研究工作,解释了各种降温方案的原理。还提出了一种变截面同心筒的设计方案,即将同心筒内外筒的间隙设计成收缩-扩张形状(类似于拉瓦尔喷管),利用此变截面同心筒对气流的加速作用来提高燃气的出流速度,以达到降低高温燃气温度的目的。文中用FLUENT对设计结构进行了二维数值模拟,验证了可行性,显示出此方案可在一定程度上改善导弹工作时的热环境。
In order to improve the hot environment that faces missiles launched by concentric canister launcher（ CCL）, the factors that affect the gas temperature at the outlet of CCL are discussed and the fundamental gasdynamics principle in the process of reducing gas temperature are also analyzed in this paper. And several research works for reducing outlet gas temperature of CCL are analyzed with the energy conservation theory in the paper, several kinds of CCL developed by others are explained in detail about how to reduce gas temperature at the outlet of CCL. Furthermore, a new type, variable crosssection concentric canister launcher, is proposed in the paper. The gap between outer and inter canisters of the launcher is designed to be a convergent-divergent shape similar to the Laval nozzle to enhance the outlet velocity of gas while reduce its temperature. FLUENT software is used to numerically simulate a 2-D convergant-divergent type CCL. The simulation results show that the eonvergant-divergent type CCL can improve the missiles faced hot environment.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2013年第9期1281-1287,共7页
Journal of Astronautics
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
同心筒发射装置
扩张收缩间隙
高温燃气射流
热环境
气体动力学原理
Concentric canister launcher （CCL）
Convergent-divergent gap
High temperature gas jet
Hot environment
Gas dynamics principle
