母弹斜尾翼对子弹散布影响的计算与试验研究  

Calculate and Experimental Study on the Influence of the Main Rocket Inclined Tails on the Sub Projectiles Drops' Character

作　　者：郑延斌[1] 李小军[2] 郭光全 吕慧贞 陈智刚[1] 赵太勇[1] 

机构地区：[1]中北大学地下目标毁伤技术国防重点学科实验室,太原030051 [2]中国人民解放军防化研究院,北京102205 [3]晋西工业集团,太原030051

出　　处：《科学技术与工程》2015年第7期195-199,共5页Science Technology and Engineering

摘　　要：母弹转速对子弹散布是一个不利的影响,为了减小这种不利影响,设计了斜置尾翼。在保证母弹飞行稳定性的前提条件下选择了最小的尾翼安装角,使飞行时尾翼产生的滚转力矩最小,从而飞行时母弹的平衡转速降至最低,将母弹转速对子弹抛撒的不利影响降到最低。同时还为子弹的抛撒设计了时序性。试验表明,在该斜置尾翼安装角及1.5 s的时序性下,子弹的散布情况良好,子弹散布的可控性得到了提高,能很好的满足子弹群的杀伤效能,有一定的实际应用价值。Main rocket＇ s rotating speed is an unfavorable influence to sub munitions＇spread. Reduce this unfavorable influence, inclined tails were designed. The Least tail installation angle was selected under the condition that the main rocket flies steady to reduce the rolling moment maximizing the tails produce while flying, so that the main rocket＇s balancing rotating speed decreased to least while flying, this make the unfavorable influence drop to the lowest. At the same time, time sequence was designed for sub munitions＇ dispersing. The experiment proves that sub munitions drops characters are good under this tail angle and time sequence of 1.5 s, controllability of sub munitions drops character has been improved, content the sub projectiles inflict causalities efficacy well. There is a certain practical value.

关 键 词：母弹转速 子弹散布 斜置尾翼 时序性 

分 类 号：TJ510.33[兵器科学与技术—军事化学与烟火技术]