Analysis of Multi-field Coupling Characteristics of Rocket Sled with a Wingless Payload

doi:10.12382/bgxb.2024.0394

Abstract

Abstract:

Wingless payload is a common type of payload in the rocket sled test system,which is susceptible to head-up and head-down phenomena during separation due to the multi-field coupling of unsteady aerodynamics,vibration and aeroacoustic noise during the horizontal running in a wide speed domain.The,acoustic-vibration force coupling of horizontal boost glide in a wide speed domain ( Mach number of 0.4-2.0) is numerically simulated by taking a wingless payload test system of double-track rocket sled as the research object.The results show that a low-pressure region is generated between the payload and the booster during running,and the range of action is continuously expanded with the running speed.The aerodynamic load of high-speed flow field gradually makes the rocket sled produce large deformation at the head and tail positions of the payload,which is mainly manifested as a “head-up” phenomenon.The aerodynamic noise of the horizontal booster running in the wide speed domain increases with the running speed,and the high sound pressure level region gradually expands from the center to the periphery.The relevant research can provide technical support for the design of new generation of hypersonic rocket sled test system and the high-precision ground dynamic test.

Key words: rocket sled, horizontal running, multi-field coupling, aerodynamic characteristics, aeroacoustic noise characteristics

CLC Number:

V211.3

WANG Wenjie, MA Xinyu, ZHAO Xu, LI Haojun, XIANG Yue, YANG Long. Analysis of Multi-field Coupling Characteristics of Rocket Sled with a Wingless Payload[J]. Acta Armamentarii, 2025, 46(4): 240394-.

Figures/Tables 22

Fig.1 Side view of rocket sled system

Fig.2 AGARD HB-2 standard model

Fig.3 Global mesh

Fig.4 Local mesh

Fig.5 Mesh independence validation

Fig.6 Pressure distributions of flow field at different running speeds

Fig.7 Streamline distribution of flow field around the rocket sled

Fig.8 Variation of resistance coefficient and lift coefficient at different running speeds

Fig.9 Variation of payload pitching moment at different running speeds

Fig.10 Payload head pressure distribution

Fig.11 Payload thin-walled structure dimensions

Fig.12 Booster thin-walled structure dimensions

Fig.13 Solid structure computational mesh

Table 1 Structural material parameters of rocket skid

参数	数值
密度/(kg·m^-3)	7850
弹性模量/MPa	2.1×10⁵
剪切模量/MPa	7.7×10⁴
泊松比	0.3
压缩屈服强度/MPa	250
压缩极限屈服强度/MPa	460

Fig.14 Total deformation distribution of rocket sled at different running speeds

Table 2 Maximum deformations in both directions at different running speeds

Ma	最大竖向变形/mm	最大横向变形/mm
0.6	0.18	0.10
1.2	0.62	0.35
2.0	2.03	0.98

Fig.15 Equivalent stress distribution of rocket sled at different running speeds

Table 3 The maximum equivalent stress and maximum deformation of the sled under different working conditions

滑跑速度 Ma	最大应力/ MPa	最大应力位置	最大变形量/mm	最大变形位置
0.6	30.6	后连接与助推器接触处	0.22	有效载荷尾部
1.2	156.0	后连接与助推器接触处	1.03	有效载荷尾部
2.0	329.4	前连接与助推器接触处	2.21	有效载荷头部

Fig.16 Noise receiver on a plane

Fig.17 Sound power spectral density distribution at characteristic receiving points at different running speeds

Fig.18 Cloud image of total sound pressure on symmetric surface at different running speeds

Fig.19 Sound directivity on the monitoring plane

References 32

[1]	陈科儒, 孙琨, 陈诚, 等. 高超声速火箭橇凿削磨损机理分析[J]. 西安交通大学学报, 2024, 58(8): 136-144.
	CHEN K R, SUN K, CHEN C, et al. Analysis of gouging wear mechanism of hypersonic rocket sled[J]. Journal of Xi’an Jiaotong University, 2024, 58(8):136-144. (in Chinese)
[2]	孙宗祥, 李文佳, 唐志共, 等. 美国空气动力地面试验能力及发展趋势分析[J]. 空气动力学学报, 2023, 41(1):1-21.
	SUN Z X, LI W J, TANG Z G, et al. The capability aerodynamic ground test in the USA and its development trend analysis[J]. Acta Aerodynamica Sinica, 2023, 41(1):1-21. (in Chinese)
[3]	夏有财, 徐进新, 耿强, 等. 火箭橇试验系统研究现状与趋势[C]// 中国航天第三专业信息网第四十届技术交流会暨第四届空天动力联合会议论文集——S01固体推进及相关技术. 华阴: 中国华阴兵器试验中心, 2019.
	XIA Y C, XU J X, GENG Q, et al. Rocket sled test system research status and trends[C]// Proceedings of the 40th Technical Exchange Conference of the Third Professional Information Network of Chinese Aerospace Industry and the 4th Joint Conference of Space Power,S01 Solid Propulsion and Related Technologies. Huayin: China Huayin Weapon Test Center, 2019. (in Chinese)
[4]	杨依峰, 周人歌, 吴乔, 等. 单轨火箭橇跨声速试验复杂流动研究[J]. 工程技术研究, 2021, 6(11):11-13.
	YANG Y F, ZHOU R G, WU Q, et al. Complex flow study of monorail rocket sled transonic test[J]. Engineering and Technological Research, 2021, 6(11):11-13. (in Chinese)
[5]	房明, 孙建红, 王从磊, 等. 低亚声速火箭橇尾流场特性分析[J]. 空气动力学学报, 2017, 35(6):897-901.
	FANG M, SUN J H, WANG C L, et al. Analysis of wake flow characteristics for flow subsonic rocket sled[J]. Acta Aerodynamica Sinica, 2017, 35(6):897-901. (in Chinese)
[6]	余元元, 王方元, 王彬, 等. 超声速火箭橇流动特征和气动力激励振动分析[J]. 西北工业大学学报, 2022, 40(5):1080-1089.
	YU Y Y, WANG F Y, WANG B, et al. Analysis on flow characteristics and aerodynamic-force-induced vibration of supersonic rocket-sled[J]. Journal of Northwestern Polytechnical University, 2022, 40(5):1080-1089. (in Chinese)
[7]	WALIA S, SATYA V, MALIK S, et al. Rocket sled based high speed rail track test facilities:a review[J]. Defence Science Journal, 2022, 72(2):182-194.
[8]	GOTO K, KATO Y, ISHIHARA K, et al. Thrust validation of rotating detonation engine system by moving rocket sled test[J]. Journal of Propulsion and Power, 2021, 37(3):419-425.
[9]	王健. 高速火箭橇—轨道系统耦合动力学研究[D]. 南京: 南京理工大学, 2012.
	WANG J. The research for coupled dynamic of high speed rocket sled-track systems[D]. Nanjing: Nanjing University of Science and Technology, 2012. (in Chinese)
[10]	王文杰, 赵旭, 杨龙, 等. 跨速域强地效水平助推滑跑气动机理[J]. 航空学报, 2023, 44(21):528247.
	WANG W J, ZHAO X, YANG L, et al. Aerodynamic mechanism of strong ground effect on horizontal boost run cross velocity domain[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(21):528247. (in Chinese)
[11]	何磊, 刘灿萍. 航宇再创双轨火箭橇试验速度新纪录[N]. 中国航空报,2022-05-06(003).
	HE L, LIU C P. Aerospace sets another new speed record for dual-orbit rocket sled test[N]. China Aviation News,2022-05-06(003). (in Chinese)
[12]	ROBERT E, PAWEL, STEVEN J, et al. Computational aeroelastic analysis of the Ares I arew launch vehicle during ascent[J]. Journal of spacecraft and rockets, 2012, 49(4):651-658.
[13]	LOFTHOUSE A, HUGHSON M, PALAZOTTO A, et al. Computational aerodynamic analysis of the flow field about a hypervelocity test sled[C]// Proceedings of the 41st Aerospace Sciences Meeting and Exhibit.Reno,NV, US: AIAA, 2003.
[14]	DANG T J, LI B F, HU D K, et al. Aerodynamic design optimization of a hypersonic rocket sled deflector using the free-form deformation technique[J]. Proceedings of the Institution of Mechanical Engineers, Part G:Journal of Aerospace Engineering, 2021, 235(15):2240-2248.
[15]	YU Y Y, WANG B, XU C Y, et al. Aerodynamic characteristics of supersonic rocket-sled involving waverider geometry[J]. Applied Sciences, 2022, 12(15):7861.
[16]	邹伟红. 火箭滑橇空气动力的数值模拟[D]. 南京: 南京理工大学, 2008.
	ZHOU W H. Numerical simulation of rocket sled aerodynamics[D]. Nanjing: Nanjing University of Science and Technology, 2008. (in Chinese)
[17]	施方成, 高振勋, 田雨岩, 等. 超声速理想膨胀喷流噪声的大涡模拟[J]. 航空学报, 2023, 44(2):107-125.
	SHI F C, GAO Z X, TIAN Y Y, et al. Large eddy simulation of ideally expanded supersonic jet noise[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(2):107-125. (in Chinese)
[18]	刘俊, 蔡晋生, 杨党国, 等. 超声速空腔流动波系演化及噪声控制研究进展[J]. 航空学报, 2018, 39(11):18-36.
	LIU J, CAI J S, YANG D G, et al. Research progress in wave evolution and noise control for supersonic cavity flows[J]. Acta Aeronautica et Astronautica Sinica, 2018, 39(11):18-36. (in Chinese)
[19]	卢清华, 陈宝. 基于LES方法的增升装置气动噪声特性分析[J]. 空气动力学学报, 2016, 34(4):448-455.
	LU Q H, CHEN B. Analysis of aeroacoustics characteristics of high lift device using LES method[J]. Acta Aeronautica et Astronautica Sinica, 2016, 34(4):448-455. (in Chinese)
[20]	JAMALUDDIN N S, CELIK A, BASKARAN K, et al. Aerodynamic noise analysis of tilting rotor in edgewise flow conditions[J]. Journal of Sound and Vibration, 2024,582:118423.
[21]	DOIG G. Transonic and supersonic ground effect aerodynamics[J]. Progress in Aerospace Sciences, 2014,69:1-28.
[22]	YADEGARI M, OMMI F, SABOOHI Z, et al. Synergy between noise reduction techniques applied in different industries:a review[J]. The International Journal of Multiphysics, 2020, 14(2):161-192.
[23]	张婷婷, 叶瑞, 姜维, 等. 高超声速风洞HSCM系列标准模型气动力实验数据[J]. 气体物理, 2021, 6(4):57-65.
	ZHANG T T, YE R, JIANG W, et al. Aerodynamic test data of hscm calibration models in hypersonic wind tunnel[J]. Physics of Gases, 2021, 6(4):57-65. (in Chinese)
[24]	黄长强, 国海峰, 唐上钦, 等. 超音速带弹武器舱气动特性数值研究[J]. 兵工学报, 2013, 34(8):975-980.
	HUANG C Q, GUO H F, TANG S Q, et al. Numerical research on aerodynamic characteristics of cavity with store at supersonic speeds[J]. Acta Armamentarii, 2013, 34(8):975-980. (in Chinese)
[25]	熊志平, 武晓松, 夏强, 等. 超声速轴对称进气道流场的数值模拟[J]. 兵工学报, 2009, 30(1):5-8.
	XIONG Z P, WU X S, XIA Q, et al. Numerical simulation of supersonic axisymmetric inlet flow field[J]. Acta Armamentarii, 2009, 30(1):5-8. (in Chinese)
[26]	YUSUF S N A, ASAKO Y, SIDIK N A C, et al. A short review on rans turbulence models[J]. CFD Letters, 2020, 12(11):83-96.
[27]	葛向东, 吴法勇, 刘永泉, 等. 航空发动机整机振动问题研究方法及工程应用[J]. 航空学报, 2024, 45(4):36-56.
	GE X D, WU F Y, LIU Y Q, et al. Research methods for whole aeroengine vibration and their engineering application[J]. Acta Aeronautica et Astronautica Sinica, 2024, 45(4):36-56. (in Chinese)
[28]	张晨曦, 林三春, 李易, 等. 反向射流作用下可回收火箭升阻特性[J]. 哈尔滨工业大学学报, 2024, 56 (4):24-30.
	ZHANG C X, LIN S C, LI Y, et al. Lift-to-drag characteristics of the propulsive descent stage of reusable rockets[J]. Journal of Harbin Institute of Technology, 2024, 56(4):24-30. (in Chinese)
[29]	黄乾. 基于大涡模拟的锯齿尾缘翼型流动分析及气动噪声预测[D]. 北京: 清华大学, 2016.
	HUANG Q. A numerical study of the flow around airfoils with serrated trailing edges and the aerodynamic noise based on large eddy simulation[D]. Beijing: Tsinghua University, 2016. (in Chinese)
[30]	刘莉, 孟军辉, 岳振江, 等. 飞行器结构力学[M]. 北京: 科学出版社, 2022:89-90.
	LIU L, MENG J H, YUE Z J, et al. Structural mechanics of aircraft[M]. Beijing: Science Press, 2022:89-90. (in Chinese)
[31]	袭祥发. 超空泡导弹潜射出水过程流固耦合数值研究[D]. 哈尔滨: 哈尔滨工业大学, 2022.
	GONG X F. Numerical study of fluid-structure interaction in the water-exit process of supercavitating missile[D]. Harbin: Harbin Institute of Technology, 2022. (in Chinese)
[32]	蔡建程, 刘志宏, 曾向阳, 等. 气动声学Lighthill方程的Kirchhoff积分解分析[J]. 声学技术, 2014, 33(2):99-103.
	CAI J C, LIU Z H, ZENG X Y, et al. An analysis of the Kirchhoff integral approach to the Lighthill equation in aeroacoustics[J]. Technical Acoustics, 2014, 33(2):99-103. (in Chinese)