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Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 2: 176 - 183

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.007

Multifunctional Fairing Mechanism Design Method for the Tube-launched Air-to-ground Missile

  • LI Zeyang , 1, 2 ,
  • ZHAO Guohong , 3 ,
  • PANG Yu 2 ,
  • FU Xiaowu 1, 2 ,
  • YU Lei 1, 2 ,
  • XIE Zhongliang 4
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  • 1 National Key Laboratory of Land & Air Based Information Perception and Control, Xi'an 710065, Shaanxi, China
  • 2 Xi'an Modern Control Technology Research Institute, Xi'an 710065, Shaanxi, China
  • 3 Norinco Group Testing and Research Institute, Xi'an 710000, Shaanxi, China
  • 4 School of Mechanics, Civil Engineering and Architecture, Northwestern Polytechnical University, Xi'an 710072, Shaanxi, China

Received date: 2024-11-22

  Online published: 2025-05-15

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Abstract

For the tube-launched missiles carried on air based platforms, the launchers equipped with traditional flat sealing film lead to unavoidable issues that aerodynamic drag increases and broken fairing threatens the safety of aircraft. To address the problem, the influences of the aspect ratio of ellipsoidal fairing and aircraft cruising speed on its aerodynamic characteristics are studied. The relationship between fairing aerodynamic moment and increment of rotation angle is established. Based on the model of twins torsional spring, a fairing mechanism with tandem torsional springs is designed. The analytical model for the contact force of fairing adapter and its contact point parameters is established to obtain the optimal contact point and the minimum contact force. As a result, a multifunctional fairing mechanism is proposed which is capable of reducing aerodynamic drag, nondestructively opening, reducing contact force and automatically resetting itself. The analysis results of the virtual prototype indicate that the dynamic contact force of the adapter and the reset time are respectively 224.0 N and 17.7 ms, it verifies the rationality and feasibility of the mechanism. The proposed method has important reference significance for the design of launch tube fairing of tube-launched missiles equipped on aircraft platform.

Key words： multifunctional fairing; aerodynamic characteristic; resetting mechanism; contact force; numerical simulation

Cite this article

LI Zeyang , ZHAO Guohong , PANG Yu , FU Xiaowu , YU Lei , XIE Zhongliang . Multifunctional Fairing Mechanism Design Method for the Tube-launched Air-to-ground Missile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(2) : 176 -183 . DOI: 10.15892/j.cnki.djzdxb.2025.02.007

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References

Publishing order | Descend order by publishing year | Descend order by cited within
[1]
李端松, 张大治, 张登, 等. 我国直升机载导弹发射装置的研究现状及发展趋势[J]. 弹箭与制导学报, 2018, 38(5): 35-38.

LI D S, ZHANG D Z, ZHANG D, et al. Research status and development trend of helicopter-borne missile launcher in China[J]. Journal of Projectiles, Rockets, Misssiles and Guidance, 2018, 38(5), 35-38.

[2]
黄得刚, 杜晨慧, 徐志强, 等. 国外无人机机载空面轻型弹药发展现状及趋势分析[J]. 飞航导弹, 2021(4): 63-67.

HUANG D G, DU C H, XU Z Q, et al. Development status and trend analysis of airborne light ammunition for foreign unmanned aerial vehicles[J]. Aerodynamic Missile Journal, 2021(4): 63-67.

[3]
KNAPP D J, MILLS J P, HEGG R G, et al. Conformal optics risk reduction demonstration[C]//The International Society for Optical Engineering. Proceedings of SPIE, Apr 16-17, 2001, Orlando, Florida. Bellevue: The International Society for Optical Engineering, 2001:146-153.

[4]
李东熙, 卢振武, 孙强, 等. 利用Wassermann-Wolf原理设计共形光学系统[J]. 光子学报, 2008(4): 776-779.

LI D X, LU Z W, SUN Q, et al. Research on conformal optical system design using Wassermann-Wolf principle[J]. Acta Photonica Sinica, 2008(4): 776-779.

[5]
LOPEZ D, DOMÍNGUEZ D, GONZALO J. Optimization of air-ejected rocket/missile geometries under validated supersonic flow field simulations[C]// American Institute of Physics. ICNPAA 2014, Jul 15-18, 2014, Narvik, Norway. New York: AIP Proceeding, 2014: 227-230.

[6]
LI Q, XU S, YU K, et al. Design of the compact off-axis four-mirror optical system with conformal fairing[C]//SPIE. Optical Manufacturing and Testing XII, Aug 20-22, 2018, San Diego, California. Washington: SPIE, 2018:489-492.

[7]
于婷婷. 高速飞行器椭球形整流罩特性研究[D]. 哈尔滨: 哈尔滨工业大学, 2021.

YU T T. Research on characteristics of ellipsoidal fairing for high-speed aircraft[D]. Harbin: Harbin Institute of Technology, 2021.

[8]
李福巍, 赵虹霞, 潘国庆, 等. 中波红外导弹用高强纳米红外陶瓷整流罩特性研究[J]. 光学学报, 2021, 41(7): 110-115.

LI F W, ZHAO H X, PAN G Q, et al. Study on characteristics of high-strength nano infrared ceramic dome for mid-infrared missile[J]. Acta Optica Sinica, 2021, 41(7): 110-115.

[9]
ZHU X C, LI H Y, YU T X, et al. Research on reliability analysis for low-altitude and high-speed payload fairing separation[C]//University of Electronic Science and Technology of China.Proceedings of the International Conference on Quality, Reliability, Risk, Maintenance, and Safety Engineering, July 15-18, 2013, Emeishan, China. Chengdu: University of Electronic Science and Technology of China, 2013:90-94.

[10]
赵瑞, 荣吉利, 李跃军, 等. 整流罩母线形状对脉动压力环境的影响研究[J]. 兵工学报, 2017, 38(5): 1020-1026.

DOI

ZHAO R, RONG J L, LI Y J, et al. An investigation of fluctuating pressure environment around rocket fairing with different curvetypes[J]. Acta Armamentarii, 2017, 38(5): 1020-1026.

DOI

[11]
刘浩, 李钧, 冯刚. 一种可回收火箭验证机整流罩气动外形优化[J]. 飞行力学, 2024, 42(2): 49-53.

LIU H, LI J, FENG G. Aerodynamic shape optimization for the demonstration recoverable rocket fairing[J]. Flight Dynamics, 2024, 42(2): 49-53.

[12]
赵海龙. 电磁发射固体运载火箭气动减阻设计与优化[D]. 长沙: 国防科技大学, 2020.

ZHAO H L. Aerodynamic drag reduction design and optimization of electromagnetic launch solid carrier rocket[D]. Changsha: National University of Defense Technology, 2020.

[13]
尹莲花, 骆洪志, 吴会强, 等. 冯·卡门曲面整流罩PMI泡沫夹层防热结构技术研究[J]. 导弹与航天运载技术, 2021 (3): 43-46.

YIN L H, LUO H Z, WU H Q, et al. Research of the thermal protection-structure technique by Von-Karman Fairing with PMI foam sandwich structure[J]. Missiles and Space Vehicles, 2021 (3): 43-46.

[14]
樊宇翔, 于洋, 席柯, 等. 火箭整流罩脉动压力环境数值模拟与优化设计[J]. 空气动力学学报, 2022, 40(6): 29-37.

FAN Y X, YU Y, XI K, et al. Numerical simulation and optimization design of fluctuation pressure environment of a rocket fairing[J]. Acta Aerodynamica Sinica, 2022, 40(6): 29-37.

[15]
闫指江, 吴彦森, 宫宇昆, 等. 整流罩头部钝度比对运载火箭气动性能影响研究[J]. 导弹与航天运载技术, 2020(4): 35-38.

YAN Z J, WU Y S, GONG Y K, et al. Study on the influence of blunt ratio of fairing head on aerodynamic performance of launch vehicle[J]. Missiles and Space Vehicles, 2020(4): 35-38.

[16]
张玉东, 纪楚群. 多体分离非定常气动特性数值模拟[J]. 空气动力学学报, 2006(1): 1-4.

ZHANG Y D, JI C Q. The numerical simulation of unsteady multi-body separation flows[J]. Acta Aerodynamica Sinica, 2006(1): 1-4.

[17]
成大先. 机械设计手册:第3卷[M]. 5版. 北京: 化学工业出版社, 2007.

CHENG D X. Handbook of mechanical design:volume 3[M]. 5th ed. Beijing: Chemical Industry Press, 2007.

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