摘要
设计适用于小口径榴弹的分层三片式阻力修正执行机构,利用虚拟样机软件验证阻力机构的可靠性;建立阻力执行机构安装在不同位置、不同展开高度的修正弹模型;利用计算流体力学软件对不同弹丸模型进行绕流流场数值模拟,获得其在不同马赫数、不同攻角情况下的气动力参数并分析其飞行稳定性。结果表明,阻尼片能够顺利展开,可以为修正弹提供的阻力系数比值范围为:1.86~5.19。
This design stratified three piece type＇s correction executive mechanism suitable for the small caliber grenade,verify its reliability using virtual prototype software; numerical simulation taken for different projectile model with correction execution mechanism installed in different position,different expansion height,obtain the air dynamic parameters and analysis its flying stability in different mach numbers and different angle of attack. Results show that the damping fins can unfold smoothly,range of drag coefficient ratio provided for trajectory correction projectiles is： 1. 86 - 5. 19.
出处
《兵器装备工程学报》
CAS
2017年第12期102-105,共4页
Journal of Ordnance Equipment Engineering
基金
瞬态冲击技术重点实验室基金(61426060101)
山西省研究生联合培养基地人才培养项目(20160033,20170028)
关键词
弹道修正
修正执行机构
数值仿真
trajectory correction
correction executive mechanism
numerical simulation
