导弹发射管内燃气流场的实验分析  

Experimental analysis of exhausted flow field in closed container-launcher

作　　者：徐强[1] 廖光煊[1] 李军[2] 

机构地区：[1]中国科学技术大学火灾科学国家重点实验室,安徽合肥230026 [2]南京理工大学机械学院,江苏南京210094

出　　处：《推进技术》2001年第5期361-363,共3页Journal of Propulsion Technology

摘　　要：针对密封盖未及时开启造成发射装置的损坏问题进行了实验分析。实验测量了对发射管壁静压和密封盖受到的燃气射流冲击压力 ,利用子波分析方法求取了实验数据的基于子波系数的频带能量谱 ,并对含有射流噪声的测量数据进行了子波滤波 ,得到了各点压力低频成分的变化情况 ,同时得到了密封盖所受冲击冲量与激波振荡幅值的关系。研究表明密封盖不及时开启会在弹管间隙中形成高幅值的起始冲击波和燃气回流激波振荡。这种破坏性的流动结构会导致发射装置的损坏。Experimental analysis was conducted to study launching equipment damage caused by open-delay of air-proof cover. Static pressure on the launch tube wall and shock pressure on the air-proof cover were measured in experiment. Wavelet analysis was applied to obtain frequency band energy spectrum of pressure data based on wavelet coefficient. Pressure changing with low frequency was extracted by wavelet filter. The relationship between shock impulse on the cover and amplitude of shock oscillation was also obtained. Study results show that harmful flow structure caused by open-delay of the cover with initial shock wave and shock oscillation has significant amplitude in the clearance between rocket and launch tube, this would cause damage to launching equipment.

关 键 词：导弹发射管 喷管气流 流动分布 子波分析 冲击波 激波振荡 

分 类 号：TJ768.2[兵器科学与技术—武器系统与运用工程] TJ760.11