[1]单继祥,赵 平,龚志斌,等.基于气动/弹道耦合的激波针外形优化研究[J].弹道学报,2020,32(02):1-6.[doi:10.12115/j.issn.1004-499X(2020)02-001]
 SHAN Jixiang,ZHAO Ping,GONG Zhibin,et al.Design Optimization of Spikes Based on Aerodynamic-ballisticCoupling Method[J].Journal Of Ballistics,2020,32(02):1-6.[doi:10.12115/j.issn.1004-499X(2020)02-001]
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基于气动/弹道耦合的激波针外形优化研究()
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《弹道学报》[ISSN:1004-499X/CN:32-1343/TJ]

卷:
32
期数:
2020年02期
页码:
1-6
栏目:
出版日期:
2020-06-30

文章信息/Info

Title:
Design Optimization of Spikes Based on Aerodynamic-ballisticCoupling Method
文章编号:
1004-499X(2020)02-0001-06
作者:
单继祥赵 平龚志斌陈强洪
中国工程物理研究院 总体工程研究所,四川 绵阳 621999
Author(s):
SHAN JixiangZHAO PingGONG ZhibinCHEN Qianghong
Institute of System Engineering,China Academy of Engineering Physics,Mianyang 621999,China
关键词:
激波针 阻力特性 落地速度 气动/弹道耦合 优化
Keywords:
spike drag characteristic landing velocity aerodynamic-ballistic coupling method optimization
分类号:
TJ303.4
DOI:
10.12115/j.issn.1004-499X(2020)02-001
文献标志码:
A
摘要:
为了优化钝形弹头激波针外形设计,在超声速条件下实现显著减小气动阻力,有效提高全弹飞行速度的目的,采用数值模拟方法研究了亚、跨、超声速范围内球头激波针外形参数对减阻效果的影响及其流动机理,并以最大落地速度为优化目标,基于气动/弹道耦合方法对激波针外形参数进行了优化。结果表明:亚、跨声速范围内,由于激波针产生的附加阻力较大,使得全弹阻力系数增大,激波针无减阻效果; 超声速时,激波针的减阻效果明显,且随马赫数的增大,最佳减阻外形的长度增大,半径减小。基于气动/弹道耦合的激波针外形优化方法充分考虑了气动阻力对飞行弹道的影响,优化后全弹落地速度、射程增幅提高10.0%左右。同时,在计算范围内增加激波针对全弹升力特性、静稳定性的影响均较小。
Abstract:
The spike installed on the blunt-nosed body pushes the strong bow shock away from the body surface in supersonic speed,which forms recirculation flow with low pressure ahead of the body surface,and then decreases the drag,and the landing velocity of the rocket can be increased. Aiming at this problem,the effect of the spikes shape parameters on the drag induction and its flow mechanism were simulated. Based on the aerodynamic-ballistic coupling method,the spikes shape parameters were optimized to increase the landing velocity. The results show that the additional drag of the spikes is larger,and there is no drag reduction in subsonic speed and transonic speed. The drag reduction of the spikes is remakable in supersonic speed,and the optimal shape lengths increases,and the radius decreases with the increase of the Mach number. Based on the coupling method considering the effect of the drag aerodynamic of the spikes on the ballistics,the landing velocity and the range after optimization can be increased by 10.0% compared with the initial shape. In the calculation range,the effect of the spikes is little on the lift characteristic and the static stability.

参考文献/References:

[1] MILICEV S S,PAVLOVIC D. Influence of spike shape at supersonic flow past blunt-nosed bodies:experimental study[J]. AIAA Journal,2002,40(5):1018-1020.
[2]涂伟,金东海. 导弹减阻杆减阻的数值仿真研究[J]. 计算机仿真,2014,31(4):87-91.
TU Wei,JIN Donghai. Numerical simulation study on missile antidrag spike drag reduction[J]. Computer Simulation,2014,31(4):87-91.(in Chinese)
[3]SRULIJES J,GNEMMI P,RUNNE K,et al. High-pressure shock tunnel experiment and CFD calculations on spike-tipped blunt bodies:AIAA-2002-2918[R]. Reston,VA,US:AIAA,2002.
[4]侯文新,吴颂平. 带激波针的超声速飞行器多目标优化设计[J]. 战术导弹技术,2015(2):23-27.
HOU Wenxin,WU Songping. Multi-objective optimization design of hypersonic spiked bodies[J]. Tactical Missile Technology,2015(2):23-27.(in Chinese)
[5]李永红,高川,唐新武. 激波针气动特性及外形参数优化研究[J]. 兵工学报,2016,37(8):1415-1420.
LI Yonghong,GAO Chuan,TANG Xinwu. Drag reduction characteristics and design optimization of spikes[J]. Acta Armamentarii,2016,37(8):1415-1420.(in Chinese)
[6]姜维. 高超声速飞行器减阻杆气动特性研究[D]. 长沙:国防科学技术大学,2012:42-45.
JIANG Wei. Investigations on aerodynamics of a spike tipped hypersonic vehicle[D]. Changsha:National University of Defense Technology,2012:42-45.(in Chinese)
[7]XUE Y,WANG L,FU S. Drag reduction and aerodynamic shape optimization for spike-tipped supersonic blunt nose[J]. Journal of Spacecraft and Rockets,2018,55(3):552-560.
[8]BUSHNELL D M. Shockwave drag deduction[J]. Annual Review of Fluid Mechanics,2004,36:81-96.
[9]AHMED M,QIN N. Metamodels for aerothermodynamic design optimization of hypersonic spiked blunt bodies[J]. Aerospace Science and Technology,2010,14(5):364-376.
[10]SAHOO D,DAS S,KUMAR P,et al. Effect of spike on steady and unsteady flow over a blunt body at supersonic speed[J]. Acta Astronaut,2016,128:521-533.

备注/Memo

备注/Memo:
收稿日期:2019-09-22
作者简介:单继祥(1983- ),男,工程师,研究方向为飞行器气动及总体设计。E-mail:sjx637@163.com。
更新日期/Last Update: 1900-01-01