摘要
为了最大限度地减小脱壳弹弹托的消极质量,本文研究了一种新型有翼弹托结构,其质量比传统"马鞍形"弹托减小了1/4.文中分析了这种有翼弹托的脱壳机理,计算了其脱壳力,对该弹托的脱壳过程进行了数值仿真。最后对采用该有翼弹托的脱壳弹进行了靶场试验,结果表明,这种有翼弹托可以保证脱壳弹在炮膛内的闭气与运动稳定性,在出炮口后能够迅速、可靠地脱壳。
In order to reduce the negative mass of the sabot, a novel sabot with wing configuration was designed. The mass of the novel sabot is only 3/4 of the saddle shape sabot. The discarding characteristic of the novel sabot was analyzed, the discarding force of the sabot was calculated, the discarding process of the novel sabot was simulated. Finally an experiment of the novel sabot was carried out, and the result validates that the novel sabot with wing configuration can discard rapidly and reliably.
出处
《兵工学报》
EI
CAS
CSCD
北大核心
2009年第6期668-671,共4页
Acta Armamentarii
关键词
航天器结构与设计
有翼弹托
弹托结构
脱壳机理
aerostat structure and design
sabot with wing configuration
structure of sabot
discarding characteristic
