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弹箭与制导学报 >

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

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

一体化弹弹托分离性能的代理优化研究

  • 高钟谱 , 1, 2 ,
  • 许和勇 , 1, 2 ,
  • 尹晋涛 3 ,
  • 蒋胜矩 3
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  • 1 西北工业大学航空学院, 陕西 西安 710072
  • 2 飞行器基础布局全国重点实验室, 陕西 西安 710072
  • 3 西安现代控制技术研究所, 陕西 西安 710065
许和勇(1980—), 男, 教授, 博士。E-mail:

高钟谱(2001—), 男, 硕士研究生。E-mail:

收稿日期: 2024-11-25

  网络出版日期: 2025-05-15

基金资助

国家自然科学基金(12472234)

收起

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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摘要

一体化弹弹托的快速分离特性对弹丸射击精度具有重要影响, 是弹托的主要设计要求之一。为提升弹托分离性能, 基于六自由度方程和URANS方程发展了适合弹托分离计算的非定常CFD方法, 并基于Kriging模型和遗传算法构建了弹托迎风窝外形代理优化框架。采用16度压缩拐角算例, 通过与实验值对比, 验证了文中CFD方法的可靠性。通过代理优化方法得到了优化后的弹托迎风窝外形, 并对比基准弹托进行了流场和分离特性分析, 揭示了优化弹托分离性能得以提升的气动机理。结果表明, 分离过程中优化弹托贴近弹丸的内表面压力衰减量显著小于基准弹托, 迎风窝的表面压力与基准弹托基本持平, 因此, 优化弹托的整体分离力显著增加, 分离横向位移提升14.86%, 分离俯仰角提升13.75%, 分离性能显著提高。

关键词： 一体化弹; 弹托分离; 六自由度仿真; 代理优化; Kriging模型

本文引用格式

高钟谱 , 许和勇 , 尹晋涛 , 蒋胜矩 . 一体化弹弹托分离性能的代理优化研究[J]. 弹箭与制导学报, 2025 , 45(2) : 159 -166 . DOI: 10.15892/j.cnki.djzdxb.2025.02.005

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

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