一种子弹攻角适应性试验方法研究  

Research on Test Method for Projectile with Attack Angle

作　　者：张韩宇[1] 王俊林[1] 李延 陈佩银[1] 余道建[1] 甄华萍[1] ZHANG Hanyu;WANG Junlin;LI Yan;CHEN Peiyin;YU Daojian;ZHEN Huaping(Beijing Institute of Space Long March Vehicle, Beijing 100076, China)

机构地区：[1]北京航天长征飞行器研究所,北京100076

出　　处：《兵器装备工程学报》2019年第S02期70-72,共3页Journal of Ordnance Equipment Engineering

摘　　要：提出了一种考核子弹攻角适应性试验方法,通过改造子弹尾翼,产生不对称阻力,实现弹丸可控的带攻角着靶;以某子弹为例,进行了气动计算、尾翼改造和试验方法设计。通过气动计算和验证,结果表明,采用本方法可使子弹飞行,攻角值可控。试验方法操作简便,易实现,试验成本低,为弹药设计研制提供参考。Due to the difference between the ground test and the flight test,the ground test cannot comprehensively assess the practical application of the ammunition,such as the damage effect of the projectile with attack angle.This paper proposes an attack angle test method.By modifying the bullet tail,an asymmetric resistance is generated,and projectile can be controlled to impact targets with a certain attack angle.Taking a projectile as an example,aerodynamic calculation,tail modification and test method design were carried out.The results of aerodynamic calculation and experimental verification show that a certain attack angle can be generated for the flying projectile by this method and the attack angle is controllable.The test method is simple to operate,easy to realize and low in cost,providing a reference for the ammunition design and development.

关 键 词：子弹 攻角 尾翼 试验 方法 

分 类 号：TJ41[兵器科学与技术—火炮、自动武器与弹药工程]