Surrogate Optimization Study for Separation Performance on Sabot of Intergrated Launch Projectile

GAO Zhongpu; XU Heyong; YIN Jintao; JIANG Shengju

doi:10.15892/j.cnki.djzdxb.2025.02.005

Journal of Projectiles, Rockets, Missiles and Guidance >

2025 , Vol. 45 >Issue 2: 159 - 166

DOI: https://doi.org/10.15892/j.cnki.djzdxb.2025.02.005

Surrogate Optimization Study for Separation Performance on Sabot of Intergrated Launch Projectile

GAO Zhongpu ^,¹^,² ,
XU Heyong ^,¹^,² ,
YIN Jintao ³ ,
JIANG Shengju ³

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¹ School of Aeronautics, Northwestern Polytechnical University, Xi'an 710072, Shaanxi, China
² National Key Laboratory of Aircraft Configuration Design, Xi'an 710072, Shaanxi, China
³ Xi'an Modern Control Technology Research Institute, Xi'an 710065, Shaanxi, China

Received date: 2024-11-25

Online published: 2025-05-15

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Abstract

The rapid separation characteristic for a sabot from its integrated launch projectile has an important impact on the projectile firing accuracy, and is one of the main design requirements about sabot. In order to improve the separation performance of the sabot, an unsteady CFD method based on six degrees of freedom equation coupled with URANS equation is created for the separation calculation of the sabot, and a surrogate optimization framework for the shape of the windward nest of the sabot is constructed based on Kriging model and genetic algorithm. A 16 degree compression corner example is used to verify the reliability of the CFD method by comparing with the experimental values. The shape of the optimized windward nest is obtained by surrogate optimization method, and the flow field and separation characteristics of the optimized sabot are compared with the initial sabot, which reveals the aerodynamic mechanism of the improved separation performance of the optimized sabot. The results show that the decrease of the pressure on the inner surface of the optimized sabot is significantly less than that of the initial sabot during the separation process, while the pressure on windward nest of the optimized sabot is basically the same as that of the initial sabot. Therefore, the overall separation force of the optimized sabot is significantly increased, with the transverse separation displacement increases by 14.86% and separation pitching angle increases by 13.75%, and the separation performance is improved.

Key words： integrated launch projectile; sabot separation; six degrees of freedom simulation; surrogate optimization; Kriging surrogate model

Cite this article

GAO Zhongpu , XU Heyong , YIN Jintao , JIANG Shengju . Surrogate Optimization Study for Separation Performance on Sabot of Intergrated Launch Projectile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2025 , 45(2) : 159 -166 . DOI: 10.15892/j.cnki.djzdxb.2025.02.005

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References

Publishing order | Descend order by publishing year | Descend order by cited within

[1]	苏子舟, 国伟, 张博, 等. 美国电磁轨道发射技术概述[J]. 飞航导弹, 2018(2): 7-10. SU Z Z, GUO W, ZHANG B, et al. Overview of electro-magnetic orbital launch technology in the United States[J]. Aerodynamic Missile Journal, 2018(2): 7-10.

[2]	杜传通, 雷彬, 金龙文, 等. 电磁轨道炮电枢技术研究进展[J]. 火炮发射与控制学报, 2017, 38(2): 94-100. DU C T, LEI B, JIN L W, et al. Research progress on armature technology in electromagnetic railgun[J]. Journal of Gun Launch & Control, 2017, 38(2): 94-100.

[3]	SCHMIDT E M, SHEAR D D. Aerodynamic interference during sabot discard[J]. AIAA Journal of Spacecraft and Rockets, 1978, 15(3): 162-167.

[4]	黄振贵, 汤祁忠, 陈志华, 等. 非零攻角和侧滑角条件下弹托不同步飞离的数值模拟[J]. 兵工学报, 2016, 37(6): 1006-1015. DOI HUANG Z G, TANG Q Z, CHEN Z H, et al. Numerical simulation on the unsynchronized discarding of sabots at non-zero angles of attack and sideslip[J]. Acta Armamentarii, 2016, 37(6): 1006-1015.

[5]	于煜斌, 张靖, 王克勤. 新型有翼弹托脱壳机理研究[J]. 兵工学报, 2009, 30(6): 668-671. YU Y B, ZHANG J, WANG K Q. Research on the discarding characteristic of a novel sabot with wing[J]. Acta Armamentarii, 2009, 30(6): 668-671.

[6]	马伟明, 鲁军勇, 李湘平. 电磁发射超高速一体化弹丸[J]. 国防科技大学学报, 2019, 41(4): 1-10. MA W M, LU J Y, LI X P. Electromagnetic launch hypervelocity integrated projectile[J]. Journal of National University of Defense Technology, 2019, 41(4): 1-10.

[7]	ERENGIL M. An aerodynamic model for symmetric sabot separation[C]//37th Aerospace Sciences Meeting and Exhibit, January 11-14, 1999, Reno, Nevada. Reston: AIAA, 1999: 992.

[8]	ERENGIL M E, ZIELINSKI A E. Effect of electromagnetic launch on armature/sabot discard[J]. IEEE Transactions on Magnetics, 2001, 37(1): 67-72.

[9]	古刚, 李宣. 一体化弹丸弹体和弹托分离特性研究[J]. 舰船科学技术, 2020, 42(15): 32-37. GU G, LI X. Research on separation characteristic of intergration launch projectile's body[J]. Ship Science and Technology, 2020, 42(15): 32-37.

[10]	刘亚杰, 孙世岩. 舰炮制导炮弹弹托分离过程非定常流场数值模拟[J]. 弹箭与制导学报, 2016, 36(4): 98-104. LIU Y J, SUN S Y. Unsteady flow numerical simulation of sabot separation for naval gun guided projectile[J]. Journal of Projectiles, Rockets, Missiles and Guidance, 2016, 36(4): 98-104.

[11]	李湘平, 鲁军勇, 冯军红, 等. 采用遗传算法的弹托迎风窝结构设计[J]. 国防科技大学学报, 2019, 41(2): 24-30. LI X P, LU J Y, FENG J H, et al. Structure design for wind's eye of sabot using genetic algorithm[J]. Journal of National University of Defense Technology, 2019, 41(2): 24-30.

[12]	韩忠华. Kriging模型及代理优化算法研究进展[J]. 航空学报, 2016, 37(11): 3197-3225. DOI HAN Z H. Kriging surrogate model and its application to design optimization:a review of recent progress[J]. Acta Aeronautica et Astronautica Sinica, 2016, 37(11): 3197-3225.

[13]	SCHMIT J R L A, FARSHI B. Some approximation concepts for structural synthesis[J], AIAA Journal, 1974, 12(5): 692-699.

[14]	GIUNTA A A, WATSON L T. A comparison of approx-imation modeling techniques: polynomial versus interp-olation models: AIAA-1998-4758[R]. Reston: AIAA, 1998.

[15]	刘宇琪, 夏天宇, 董昊, 等. 低雷诺数翼型多目标优化设计研究[J]. 南京航空航天大学学报, 2024, 56(4): 687-697. LIU Y Q, XIA T Y, DONG H, et al. Multi-objective optimization design of airfoil at low reynolds number[J]. Journal of Nanjing University of Aeronautics & Astronautics, 2024, 56(4): 687-697.

[16]	JI B, HUANG J, LU X, et al. An improved approach for reducing the dimensionality of wing aerodynamic optimi-zation considering longitudinal stability[J]. Aerospace, 2024, 11:80.

[17]	JIGAR P, PHILIP B, SEBASTIAN H, et al. Surrogate based design space exploration and exploitation for an efficient airfoil optimization under uncertainties using transition models[J]. Aerospace Science and Technology, 2024, 154: 109532.

[18]	张晓, 鲁军勇, 李湘平, 等. 电磁感应线圈发射子弹系统优化设计[J]. 电工技术学报, 2021, 36(22): 4658-4665. ZHANG X, LU J Y, LI X P, et al. System optimization of electromagnetic induction coil launch bullet[J]. Transactions of China Electrotechnical Society, 2021, 36(22): 4658-4665.

[19]	王福军. 计算流体动力学分析-CFD软件原理与应用[M]. 北京: 清华大学出版社, 2004: 7-13. WANG F J. Computational fluid dynamics analysis-principle and application of CFD software[M]. Beijing: Tsinghua University Press, 2004: 7-13.

[20]	OLIVER A B, LILLARD R P, BLAISDELL G A, et al. Validation of high-speed turbulent boundary layer and shock-boundary layer interaction computations with the OVER-FLOW Code[C]//AIAA.44th AIAA Aerospace Sciences Meeting and Exhibit, January 9-12, 2006, Reno, Nevada. Reston: AIAA, 2006: 894.

[21]	MENTER F R. Two-equation eddy-viscosity turbulence models for engineering applications[J]. AIAA Journal, 2012, 32(8): 1598-1605.

[22]	GIUNTA A A, WOJTKIEWICZ J S F, ELDRED M S. Overview of modern design of experiments methods for computational simulations: AIAA-2003-649[R]. Reston: AIAA, 2003.

[23]	HAN Z H, ZHANG K S. Surrogate-based optimization[M]. Ljubljana: InTech Book, 2012: 343-362.

[24]	LIU J, HAN Z H, SONG W P. Comparison of infill sampling criteria in kriging-based aerodynamic optimization[C]// ICAS.28th Congress of the International Council of the Aeronautical Sciences, September 23-28, 2012, Brisbane, Australia. Bonn: ICAS, 2012.

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