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弹箭与制导学报 >

2025 , Vol. 45 >Issue 6: 1310 - 1317

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.06.043

学术文章

高速火箭橇气动热预测与试验分析

  • 周学文 ,
  • 张晨辉 , * ,
  • 吕水燕 ,
  • 刘禁 ,
  • 巴玮韬
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  • 中国兵器工业试验测试研究院,陕西省华阴市 714200
张晨辉(1988—),男,副研究员,硕士研究生。E-mail:。

周学文(1979—),男,研究员,博士研究生。E-mail:。

收稿日期: 2025-05-20

  网络出版日期: 2026-01-24

基金资助

国防科技创新特区项目(20-163-16-ZD-005-007-01)

收起

Aerodynamic Heat Prediction and Experimental Analysis of High-Speed Rocket Sleds

  • ZHOU Xuewen ,
  • ZHANG Chenhui , * ,
  • LV Shuiyan ,
  • LIU Jin ,
  • BA Weitao
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  • NORINCO GROUP Test and Measuring Academy,Huayin 714200,China

Received date: 2025-05-20

  Online published: 2026-01-24

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摘要

气动热研究在火箭橇试验中具有至关重要的作用,它不仅能够为火箭橇的结构设计提供关键依据,还能确保其在高速运行中的安全性和可靠性。文章重点研究了空间离散格式、湍流模型、法向第一层网格高度等因素对气动热计算结果的影响,并以典型高速火箭橇简化模型为研究对象,开展了详细的气动热计算,通过分析橇体关键特征位置热流分布规律,揭示了轨道反射激波和整流帽对舱体侧面的干扰机制。此外,基于某单轨火箭橇试验数据,对仿真与实验结果的一致性进行了定量分析。研究结果表明:(1)火箭橇气动热预示中,空间离散格式宜选用Roe格式,湍流模型宜采用S-A模型,且法向第一层网格高度应不大于1×10-7m;(2)典型橇体中无干扰区域的热流峰值为24050kW/m2,主要集中在连接段;轨道反射激波在锥段舱体下半部分形成干扰,整流帽对舱体侧面形成明显的干扰,均使得干扰区域热流显著增大;(3)温度仿真结果与试验结果的最大偏差为17.88%,表明该数值方法可用于后续火箭橇气动热预测。本文的研究成果为火箭橇试验的工程应用提供了重要的理论支持。

关键词： 火箭橇; 数值模拟; 气动热; 热流密度; 试验验证

本文引用格式

周学文 , 张晨辉 , 吕水燕 , 刘禁 , 巴玮韬 . 高速火箭橇气动热预测与试验分析[J]. 弹箭与制导学报, 2025 , 45(6) : 1310 -1317 . DOI: 10.15892/j.cnki.djzdxb.2025.06.043

Abstract

Aerodynamic heat research plays a crucial role in rocket sled testing,providing essential support for structural design and ensuring safety and reliability during high-speed operation.This paper focuses on the impact of spatial discretization schemes,turbulence models,and the height of the first normal grid layer on aerodynamic heat calculation results.Using a simplified model of typical a high-speed rocket sled,detailed aerodynamic heat calculations were conducted.The study analyzed the heat flux distribution at key locations on the sled body,revealing the interference mechanisms caused by track-reflected shock waves and fairings on the side of the vehicle.In addition,this paper conducts a quantitative analysis of the consistency between simulation and experimental results based on data from a single-track rocket sled test.The results indicate that:(1) For aerodynamic heat prediction in rocket sled,the Roe scheme is recommended for spatial discretization,the S-A model is preferred for turbulence modeling,and the height of the first normal grid layer should not exceed 1×10-7m; (2) In the typical sled body,the peak heat flux in interference-free areas reaches 24050kW/m2,primarily concentrated in the connecting section.Interference are formed on the lower half of the conical section due to track-reflected shock waves,and significant interference is observed on the vehicle’s side due to the fairing,both of which lead to a substantial increase in local heat flux; (3) The maximum deviation between the simulated and experimental temperature results is 17.88%,demonstrating that the numerical method can be used for subsequent aerodynamic heat prediction of rocket sleds.The findings of this study provide important theoretical support for the engineering application of rocket sled testing.

Key words： rocket sled; numerical simulation; aerodynamic heat; heat flux density; experimental validation

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参考文献

原文顺序 | 文献年度倒序 | 文中引用次数倒序
[1]
景建斌, 赵卫星. 火箭橇试验[J]. 测试技术学报, 2012,26:82-91.

JING J B, ZHAO W X. Rocket sled test[J]. Journal of Testing Technology, 2012,26:82-91.

[2]
张晨辉, 杨洋, 杨珍, 等. 火箭橇试验无扰动分离技术[J]. 弹箭与制导学报, 2021, 41(02):47-50.

ZHANG C H, YANG Yang, YANG Zhen, et al. Undisturbed separation technique of rocket sled test[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2021, 41(02):47-50.

[3]
夏有财, 孔维红, 孙其会, 等. 两级推进单轨火箭橇试验研究[J]. 航空动力学报, 2025, 40(03):489-495.

XIA Y C, KONG W H, SUN Q H, et al. Experimental study on two-stage propulsion monorail rocket sled[J]. Journal of Aerospace Power, 2025, 40(03):489-495.

[4]
ZHOU X W, YAN H D, CHEN C, et al. Mechanistic study of rail gouging during hypersonic rocket sled tests[J]. Advances in Materials Science and Engineering, 2022(1):7165240.

[5]
DANG T J, LIU Z, ZHOU X W, et al. Dynamic response of a hypersonic rocket sled considering friction and wear[J]. Journal of Space craft and Rockets, 2022, 59(4):1289-1303.

[6]
赵项伟, 杨珍, 杨洋. 火箭橇靴轨接触特性数值分析[J]. 振动与冲击, 2022, 41(1):238-243.

ZHAO X W, YANG Z, YANG Y. Numerical analysis for slipper-rail contact characteristics of rocket sled[J]. Journal of Vibration and Shock, 2022, 41(1):238-243.

[7]
范孝华, 唐志共, 王刚, 等. 激波/湍流边界层干扰低频非定常性研究评述[J]. 航空学报, 2022, 43(1):625917.

DOI

FAN X H, TANG Z G, WANG G, et al. Review of low-frequency unsteadiness in shock wave/turbulent boundary layer interaction[J]. Acta Aeronautica et Astronautica Sinica, 2022, 43(1):625917.

DOI

[8]
赵雄飞, 吴国东, 王志军, 等. 超高速弹丸气动热的数值模拟[J]. 弹箭与制导学报, 2017, 37(2):108-110.

DOI

Zhao X F, Wu G D, Wang Z J, et al. Numerical Simulation of Aerodynamic Heat of Hypersonic Projectile[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2017, 37(2):108-110.

[9]
Hu B, Qu X T, Liang Fu, Yan H D. Engineering Calculation and Analysis of Aerodynamic Heating for Hypersonic Rocket Sleds[J]. Journal of Physics:Conference Series, 2023, 2478(8):082009.

DOI

[10]
王庆洋, 丛堃林, 刘丽丽, 等. 临近空间高超声速飞行器气动力及气动热研究现状[J]. 气体物理, 2017, 2(4):46-55.

WANG Q Y, CONG K L, LIU L L, et al. Research status on aerodynamic force and heat of near space hypersonic flight vehicle[J]. Physics of Gases, 2017, 2(4):46-55.

[11]
彭治雨, 石义雷, 龚红明, 等. 高超声速气动热预测技术及发展趋势[J]. 航空学报, 2015, 36(1):325-345.

DOI

PENG Z Y, SHI Y L, GONG H M, et al. Hypersonic aeroheating prediction technique and trend of development[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):325-345.

[12]
Jiang Z, Hu Z, Wang Y, et al. Advances in critical technologies for hypersonic and high-enthalpy wind tunnel[J]. Chinese Journal of Aeronautics, 2020, 33(12):3027-3038.

DOI

[13]
赵卫星, 余远锋, 闫华东. 高超声速火箭橇气动热理论分析[J]. 兵器装备工程学报, 2021, 042(S2):154-158,196.

ZHAO W X, Yu Y F, Yan H D. Theoretical analysis of aerodynamic heating for hypersonic rocket sleds[J]. Journal of Ordnance Equipment Engineering, 2021, 42(S2):154-158,196.

[14]
王志超, 张龙, 姚琳. 高速飞行器结构气动热计算与温度场模拟[J]. 四川兵工学报, 2015, 36(11):49-52.

WANG Z C, ZHANG L, YAO L. Aerodynamic heat calculation and temperature field simulation of high-speed flight vehicle structure[J]. Journal of Ordnance Equipment Engineering, 2015, 36(11):49-52.

[15]
陈鑫, 刘莉, 李昱霖, 等. 高超声速飞行器翼面气动加热的工程计算方法[J]. 弹箭与制导学报, 2013, 33(03):133-137.

CHEN X, LIU Li, LI Y L, et al. Engineering calculation method for aerodynamic heating of hypersonic vehicle wings[J]. Journal of Projectiles,Rockets,Missiles and Guidance, 2013, 33(03):133-137.

[16]
张石玉, 赵俊波, 付增良, 等. 类F-16飞行器风洞虚拟飞行试验研究[J]. 实验流体力学, 2020, 34(1):49-54.

Zhang S Y, Zhao J B, Fu Z L, et al. Wind Tunnel Based Virtual Flight Testing Research of F-16 Fighter[J]. Journal of Experiments in Fluid Mechanics, 2020, 34(1):49-54.

[17]
朱广生, 聂春生, 曹占伟, 等. 气动热环境试验及测量技术研究进展[J]. 实验流体力学, 2019, 33(02):1-10.

ZHU G S, NIE C S, CAO Z W, et al. Research progress of aerodynamic thermal environment test and measurement technology[J]. Journal of Experiments in Fluid Mechanics, 2019, 33(2):1-10.

[18]
张翔. 高超声速飞行器气动热数值模拟及优化研究[D]. 上海: 上海交通大学, 2022.

Zhang X. Numerical Simulation and Optimization of Aerodynamic Heating for Hypersonic Vehicles[D]. Shanghai: Shanghai Jiao Tong University, 2022.

[19]
薛青. 高超声速火箭气动加热数值计算方法研究[D]. 成都: 电子科技大学, 2009.

XUE Q. Numerical calculation methods for aerodynamic heating of hypersonic rockets[D]. Chengdu: University of Electronic Science and Technology of China, 2009.

[20]
吕水燕, 张传侠, 叶坤, 等. 高超声速气动热数值模拟的网格模式相关性研究[J]. 兵器装备工程学报, 2019, 40(03):82-86.

LV S Y, ZHANG C X, YE K, et al. Numerical simulation of hypersonic aerodynamic heating and grid pattern correlation[J]. Journal of Ordnance Equipment Engineering, 2019, 40(3):82-86.

[21]
吕水燕, 谢波涛, 任引艾, 等. 高超声速二维滑靴热-固耦合仿真[J]. 测试技术学报, 2014, 28(01):84-87.

LV S Y, XIE B T, REN Y A, et al. Thermo-mechanical coupling numerical simulation of hypersonic two-dimensional slider[J]. Journal of Test and Measurement Technology, 2014, 28(1):84-87.

[22]
Thomas J.Juliano, Jonathan Poggie, Kevin M.Porter, et al. “HIFiRE-5b heat flux and boundary-layer transition.” Proceedings of the 47th AIAA Fluid Dynamics Conference[J]. Reston:AIAA, 2017.

[23]
Marineau E.C., Lewis D.R., Lafferty J.F., et al. Mach 6-8 Boundary-Layer Transition Experiments on Sharp and Blunted Cones[C]//Proceedings of the 54th AIAA Aerospace Sciences Meeting. Reston:AIAA, 2016.

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