摘要
提出了一种用于超音速抛撒平头子弹药的飘带伞结构的新型超音速伞,研究弹体超音速尾流对伞气动特性的影响.在风洞试验结果验证的基础上,通过建立多套分块结构化网格模型,采用有限体积法和SST湍流模型对单独弹和伞弹分别进行超音速数值模拟,用数值纹影法显示弹体尾流场并进行了分析,得到了平头弹超音速尾流对飘带伞气动特性影响的变化规律.结果表明,弹体尾流对伞气动特性的影响随马赫数的增加而变大,随弹伞间距与弹径比和伞弹径比的增加而变小,随飘带宽度与弹径比的增加先基本保持不变后变大.
A new disk-streamer supersonic parachute and its application to supersonic dispersed flat-faced submunitions are introduced in this research. The influences of submunition＇s wake on the parachute are investigated to provide references for the design and use of the parachute. Based on the validation of wind tunnel experiment, multiple multi block grid models were built. Supersonic numerical simulations of the parachute, the submunition and their combination were conducted using finite volume method and SST turbulence model. The wake flow field of the submunition was given and analyzed by using numerical schlieren method. The influences of flat faced submunition＇s wake flow on the aerodynamic characteristics of the parachute were acquired, which could be reflected by the parachute drag coefficient. The results show that the influence increases as the Mach number increases, namely the parachute drag coefficient decreases as the Mach number increases. Also, the influence decreases as ratio of the distance between submunition and parachute to submunition＇s diameter increase as well as the ratio of parachute diameter to submunition＇s diameter increase. As for the influence of streamer width, it basically stays the same at first then increases as the streamer width increases.
出处
《北京理工大学学报》
EI
CAS
CSCD
北大核心
2011年第6期643-646,共4页
Transactions of Beijing Institute of Technology
关键词
平头弹
超音速尾流
飘带伞
气动特性
flat faced submunition
supersonic wake
disk-streamer parachute
aerodynamic characteristics
