分离涡模拟方法在内埋弹舱机弹分离模拟中的应用

李欢; 杨悦悦; 张杰; 崔鹏程; 贾洪印; 张培红

doi:10.7638/kqdlxxb-2021.0420

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分离涡模拟方法在内埋弹舱机弹分离模拟中的应用

专栏——内埋武器舱 | 更新时间：2026-05-28

- 分离涡模拟方法在内埋弹舱机弹分离模拟中的应用
- Application of DES method in internal weapon separation simulation
- 空气动力学学报 2022年40卷第3期页码：190-202
- 作者机构：
  
  中国空气动力研究与发展中心计算空气动力研究所,绵阳,621000
- 作者简介：
  
  李欢，男，助理研究员，研究方向：飞行器设计，计算空气动力学. E-mail：liyouqian2008@126.com
  贾洪印*，男，副研究员，研究方向：飞行器设计，计算空气动力学. E-mail：hongyinjia@foxmail.com
- 基金信息：
  
  国家数值风洞工程（ NNW）
- DOI：10.7638/kqdlxxb-2021.0420
  中图分类号： V211.3;TJ76
- 纸质出版：2022
- 稿件说明：
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李欢, 杨悦悦, 张杰, 等. 分离涡模拟方法在内埋弹舱机弹分离模拟中的应用[J]. 空气动力学学报, 2022, 40(3): 190−202.

LI Huan, YANG Yueyue, ZHANG Jie, et al. Application of DES method in internal weapon separation simulation[J]. 2022, 40(3): 190-202.
李欢, 杨悦悦, 张杰, 等. 分离涡模拟方法在内埋弹舱机弹分离模拟中的应用[J]. 空气动力学学报, 2022, 40(3): 190−202. DOI： 10.7638/kqdlxxb-2021.0420

LI Huan, YANG Yueyue, ZHANG Jie, et al. Application of DES method in internal weapon separation simulation[J]. 2022, 40(3): 190-202. DOI： 10.7638/kqdlxxb-2021.0420.

摘要

为了研究内埋弹舱非定常流场对武器投放分离特性的影响，基于分离涡模拟（DES）方法和非结构重叠网格技术，建立了内埋武器机弹分离高精度数值模拟方法。在此基础上，首先通过典型空腔流动和机弹分离算例验证了数值方法的有效性，然后采用平均雷诺应力模拟（RANS）和DES两种方法探究了机弹分离过程中弹舱腔内涡结构的演化历程，分析了两种方法在机弹分离流场结构模拟中的差异，研究了内埋弹舱流场结构对导弹分离特性的影响。计算结果表明：机弹分离过程中，高强度涡结构逐渐向弹舱腔体后缘聚集，同时弹舱剪切层流动结构被导弹破坏，导弹出弹舱阶段俯仰方向所受气动力矩急剧变化。相比RANS方法，DES方法捕捉到的高强度小尺度涡结构对导弹压力分布影响较大，使得分离后期导弹俯仰角、俯仰角速度产生明显差异，DES方法更适合内埋武器舱分离特性精细化研究。该研究结果可为内埋武器机弹分离研究的计算方法选择和安全分离策略提供一定的参考依据。

Abstract

In order to study the influence of unsteady flow in an internal weapons bay on the separation characteristics of the weapon release

the DES (detached-eddy simulation) method is combined with an unstructured overlapping grid technique

and a high-precision numerical simulation method for the weapon separation process is established. On this basis

the numerical method is first verified with typical examples of cavity flow and weapon separation. Then

both RANS (Reynolds-Averaged Navier-Stokes) and DES methods are used to explore the evolution of vortices in the process of internal weapon separation

and differences between the obtained flow structures are analyzed. The influence of flow structures of the embedded weapons bay on the missile separation characteristics is finally quantified. Results show that

in the separation process

high intensity vortex structures are concentrated at the trailing edge of the chamber. Meanwhile

the shear layer of the chamber is destroyed by the missile

and the aerodynamic torque in the pitch direction of the missile changes rapidly at the exit stage. Compared to the RANS result

the high-intensity small scale vortex structures captured by the DES method have a significant impact on the pressure distribution on the missile

resulting in a large difference in the pitch angle and pitch angular velocity at the late stage of separation. For this reason

DES method is more suitable for a detailed study of the separation characteristics of an internal weapons bay. The outcome of this study can provide guidance in the selection of simulation methods and safety strategies for embedded weapon separation.

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references

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