[1]向 熙,封 锋,陈 超,等.基于流-固-热耦合的超声速弹箭尾翼强度分析[J].弹道学报,2022,34(04):98-104.[doi:10.12115/j.issn.1004-499X(2022)04-014]
　XIANG Xi,FENG Feng,CHEN Chao,et al.Strength Analysis of Supersonic Rocket Projectile’s TailBased on Fluid-solid-thermal Coupling[J].Journal Of Ballistics,2022,34(04):98-104.[doi:10.12115/j.issn.1004-499X(2022)04-014]
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基于流-固-热耦合的超声速弹箭尾翼强度分析()
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《弹道学报》[ISSN:1004-499X/CN:32-1343/TJ]

卷:
34
期数:
2022年04期
页码:
98-104
栏目:
出版日期:
2022-12-31

文章信息/Info

Title:
Strength Analysis of Supersonic Rocket Projectile’s TailBased on Fluid-solid-thermal Coupling
文章编号:
1004-499X(2022)04-0098-07
作者:
向 熙1; 封 锋1; 陈 超2; 王明亮1; 罗 飞1
1.南京理工大学 机械工程学院,江苏 南京 210094; 2.安徽神剑科技股份有限公司,安徽 合肥 230601
Author(s):
XIANG Xi1; FENG Feng1; CHEN Chao2; WANG Mingliang1; LUO Fei1
1.School of Mechanical Engineering,Nanjing University of Science and Technology,Nanjing 210094,China; 2.Anhui Shenjian Technology Co.,Ltd,Hefei 230601,China
关键词:
弹箭尾翼;  流-固-热耦合;  变形;  应力;  强度分析
Keywords:
rocket tail;  fluid solid thermal coupling;  deformation;  stress;  strength analysis
分类号:
TJ714
DOI:
10.12115/j.issn.1004-499X(2022)04-014
文献标志码:
A
摘要:
为评估超声速飞行时弹箭尾翼的安全性,结合弹道曲线,计算了某型火箭弹在不同马赫数下飞行时的稳态外流场,并研究了2 s内的瞬态传热。根据传热计算的结果调整了材料的力学性能参数,进而计算了在不同飞行马赫数下,弹箭尾翼受空气动力作用产生的总变形和等效应力。结果表明:弹箭以高马赫数飞行时,前缘翼尖温度最高,且高温由该位置向内部迅速传递,马赫数越大,升温越剧烈,导致翼片前缘出现烧蚀,因此高速飞行的弹箭应对尾翼等结构进行热防护处理。高温会使材料性能下降,在气动热和气动压力共同作用下,翼片会产生较大变形,且应力可能超过许用应力。最大变形量出现在前缘翼尖,最大应力出现在翼根靠近前缘处,且都随飞行马赫数增加而增大。
Abstract:
To evaluate the safety of the rocket tail under supersonic condition,the steady-state flow field of a rocket with different Mach numbers was numerically simutated on the consideration of the ballistic curve. Then the transient heat transfer of the rocket tail in 2 s was calculated. According to the simulation results,the material mechanical property parameters of the tail was adjusted. And the total deformation and equivalent stress of the rocket tail caused by aerodynamic force in different Mach numbers was simulated. The results show that temperature of the leading edge tip is the highest on the whole tail at high Mach number conditions,and the high temperature will transmit into the within rapidly. The higher the flight Mach number is,the higher temperature of the tail is,which leading to the ablation occurs at the leading edge of the tail. Therefore,thermal protection treatment should be considered on the rocket tail under high Mach number condilion since high temperature will degrade the properties of tail’s material. Large deformation will occur on the tail and the equivalent stress may exceed allowable value under the combined action of aerodynamic heat and force. The maximum deformation which occurs at the leading edge tip and the maximum equivalent stress which occurs at the tail root near the leading edge,increase with the increase of Mach number.

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备注/Memo

备注/Memo:
收稿日期:2021-09-18
作者简介:向熙(1997- ),男,硕士研究生,研究方向为火箭弹气动特性。E-mail:xiangxi@njust.edu.cn。
通信作者:封锋(1982- ),男,副教授,研究方向为飞行器设计。E-mail:nust203@yahoo.com。
更新日期/Last Update: 2022-12-30