喷口布局对导弹侧向喷流控制作用的数值模拟

刘丽媛; 李亚超; 阎超

doi:10.13700/j.bh.1001-5965.2016.0603

喷口布局对导弹侧向喷流控制作用的数值模拟

doi: 10.13700/j.bh.1001-5965.2016.0603

1.
北京航空航天大学航空科学与工程学院, 北京 100083
2.
中国科学院力学研究所, 北京 100191

详细信息

作者简介:
刘丽媛女, 硕士研究生。主要研究方向:计算流体力学、湍流模拟

阎超男, 博士, 教授, 博士生导师。主要研究方向:空气动力学、计算流体力学

通讯作者:
阎超, E-mail:yanchao@buaa.edu.cn

中图分类号: V221⁺.3;TB553
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- 被引次数: 0
出版历程
- 收稿日期: 2016-07-18
- 录用日期: 2016-11-04
- 网络出版日期: 2017-08-20

Numerical simulation of effect of nozzle layout on jet lateral control for missiles

LIU Liyuan¹,
LI Yachao²,
YAN Chao^{1
, ,}

1.
School of Aeronautic Science and Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Institute of Mechanics, Chinese Academy of Sciences, Beijing 100191, China

More Information

Corresponding author: YAN Chao, E-mail:yanchao@buaa.edu.cn

摘要

摘要:
为保持飞行器在稀薄大气中的机动性，通常采用喷流反控制作用（RCS），但在超声速来流中，这会导致飞行器表面出现复杂的喷流干扰流场，对飞行控制造成了巨大影响。为提高对超声速条件下的侧向喷流控制作用的规律性认识，应用数值模拟方法，研究了超声速条件下的无舵光滑弹体和带尾舵的弹-翼组合体上的声速侧向喷流控制问题。开展了关于喷口布局对侧向喷流控制效果影响规律的研究工作，并通过引入法向干扰力沿程增长系数从定量角度加以分析。计算结果表明：在有尾舵的情况下，喷口位置的后移和马赫数的增加能够显著增强侧向喷流控制效果；当喷口位置位于舵面之前时，喷流干扰力放大系数随迎角增大而增大，随来流静压增大而减小；当喷流位置后移至舵面之后时，规律相反；在某些喷口位置和来流条件下，弹-翼组合体的侧向控制效果与无舵光滑弹体相比并不具备优势。
- 横向喷流 /
- 侧向控制 /
- 弹-翼组合体 /
- 喷流位置 /
- 迎角
Abstract:
In order to keep the motility in the thin atmosphere, air vehicles usually employ reaction control system (RCS), but in supersonic flow, it leads to complex jet interaction flow field on the surface of air vehicles, which has enormous influence on flight control. In order to improve the regularity understanding of jet lateral control, a model without any vane and a model with four tail vanes were used to study the sonic jet control effects in supersonic cross-flow by numerical simulation. The investigation of the influence of the jet location on the jet lateral control was conducted and the quantitative analysis of the contribution of different characteristic regions on the sweep to the jet lateral control was given. The numerical results indicate that as to wing-body configuration, the backward moving of the jet location and the increase of Mach number observably improve the jet lateral control effect; the amplification coefficient of the jet interaction force increases with the increasing angle of attack, and decreases with the increasing static pressure on condition that the jet is located before the tail vane; however, the law is opposite on condition that the jet is located after the tail vane; wing-body configuration, compared to body-alone configuration, does not have advantages on jet lateral control effects under some jet location and flow conditions.
- transverse jet /
- lateral control /
- wing-body configuration /
- jet position /
- angle of attack

HTML全文

图 1 部分带十字尾舵的弹-翼组合体模型及网格示意图

Figure 1. Schematic diagram of some wing-body configuration models and grids with a cross tail vane

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图 2 不同迎角下K_f随喷口位置的变化规律

Figure 2. Variation of K_f with jet location at different angles of attack

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图 3 不同迎角下x_e随喷口位置的变化

Figure 3. Variation of x_e with jet location at different angles of attack

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图 4 各舵面部分命名图

Figure 4. Naming sketch of each part of control surface

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图 5 各舵面C_{fin_ji}随喷口位置变化

Figure 5. Variation of C_{fin_ji} of each control surface with jet location

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图 6 不同喷口位置下的尾舵附近流场结构

Figure 6. Flow field structure near tail vane at different jet locations

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图 7 不同喷口位置情况下K_f随迎角的变化(喷口位置靠前)

Figure 7. Variation of K_f with angle of attack at different jet locations (forward positions)

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图 8 不同喷口位置情况下x_e随迎角的变化(喷口位置靠前)

Figure 8. Variation of x_e with angle of attack at different jet locations (forward positions)

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图 9 不同迎角下的流场结构对比

Figure 9. Comparison of flow field structures at different angles of attack

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图 10 不同迎角下的C_{n_ji}沿程分布

Figure 10. C_{n_ji} distribution at different angles of attack along x direction

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图 11 不同喷口位置情况下K_f随迎角的变化(喷口位置靠后)

Figure 11. Variation of K_f with angle of attack at different jet locations (backward positions)

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图 12 不同喷口位置情况下x_e随迎角的变化(喷口位置靠后)

Figure 12. Variation of x_ewith angle of attack at different jet locations (backward positions)

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图 13 不同Ma情况下K_f随喷口位置的变化

Figure 13. Variation of K_f with jet location at different Ma

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图 14 不同Ma情况下x_e随喷口位置的变化

Figure 14. Variation of x_e with jet location at different Ma

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图 15 不同Ma情况下的Ma² C_{n_ji}沿程分布

Figure 15. Ma² C_{n_ji} distribution at different Ma along x direction

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图 16 不同p_j/p_c下K_f随喷口位置的变化

Figure 16. Variation of K_f with jet location at different p_j/p_c

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图 17 不同p_j/p_c下x_e随喷口位置的变化

Figure 17. Variation of x_e with jet location at different p_j/p_c

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图 18 不同p_j/p_c下的C_{n_ji}p_c/p_j沿程分布

Figure 18. C_{n_ji}p_c/p_j distribution at different p_j/p_c along x direction

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