摘要
为研究风载荷对尾罩分离运动的影响,建立了飞行器发射模型,采用弹簧近似与网格重构相结合的非结构动网格技术,耦合求解流体力学方程及刚体六自由度运动方程,对冷弹射飞行器尾罩分离过程进行了数值模拟。通过对两种不同风速下尾罩分离非定常过程的计算,分析了风载荷对尾罩姿态角和落地距离的影响机理。结果表明:风载荷会造成尾罩俯仰角显著变化,使尾罩落地距离更远。此结果可作为设定安全距离的依据。
In order to study the influence of wind load on the separation movement of the tail cover,an aircraft launching model was established,using unstructured dynamic mesh technology of spring approximation combined with mesh reconstruction,rigid coupling solution hydrodynamic equations and the equations of motion six degrees of freedom,the numerical simulation of the separation process of tail cover of the cold launching was carried out.By calculating the unsteady process of the tail cover separation under two different wind speeds,the influence mechanism of wind load on the attitude angle and landing distance of the tail cover is analyzed.The results show that the wind load will cause a significant change in the pitch angle of the tail cover,which will make the tail cover farther away.This result can be used as the basis for setting the safety distance.
作者
孙伟
陈泽栋
SUN Wei;CHEN Zedong(No.91550 Unit,LiaoningDalian 116000,China;Department of Engineering Mechanics,Dalian University of Technology,Liaoning Dalian 116024,China)
出处
《弹箭与制导学报》
北大核心
2019年第6期102-106,共5页
Journal of Projectiles,Rockets,Missiles and Guidance
基金
国家重点基础研究发展计划(2016YFB0200702)
国家自然科学基金(91541117)资助。
关键词
尾罩分离
风载荷
非结构动网格
俯仰角
落地距离
separation of tail cover
wind load
unstructured dynamic mesh
pitch angle
landing distance
