内外流一体内埋载荷分离特性研究

周宇轩; 肖天航; 熊庆荣; 李博; 郭静亮

doi:10.13224/j.cnki.jasp.20240076

内外流一体内埋载荷分离特性研究

doi: 10.13224/j.cnki.jasp.20240076

1.
南京航空航天大学航空学院，南京 210016
2.
中国兵器工业集团有限公司西安现代控制技术研究所，西安 710065
3.
南京航空航天大学能源与动力学院，南京 210016
4.
湖南山河华宇航空科技有限公司，湖南株洲 412000

基金项目: 湖南创新型省份建设专项经费资助（2021GK1020）

详细信息

作者简介:
周宇轩（1997-），男，硕士生，研究方向为飞行器设计。E-mail：zyxzyx@nuaa.edu.cn

中图分类号: V211.3
计量
- 文章访问数: 377
- HTML浏览量: 280
- PDF量: 22
- 被引次数: 0
出版历程
- 收稿日期: 2024-02-04
- 网络出版日期: 2025-09-24

Study on embedded payload separation by using integrative computation of internal and external flows

1.
College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
2.
Xi’an Modern Control Technology Research Institute，China North Industries Group Corporation Limited，Xi’an 710065，China
3.
College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing Hunan 210016，China
4.
Hunan Shanhe Huayu Aviation Technology Limited Liability Company，Zhuzhou Hunan 412000，China

摘要

摘要:
针对由于工程约束，载荷舱布置于进气道前端的内外流一体载荷投放分离问题，运用计算空气动力学耦合六自由度运动模型、动态嵌套网格以及内外流一体建模策略，开展内外流一体的载荷投放分离非定常流场数值模拟研究，分析评估内外流一体条件下的载荷投放分离运动特性及对内流进气道流场的影响。结果表明：综合考虑载荷分离安全及其对进气道流场影响程度，分散投放方案较为稳妥；两点对称投放方案则使得进气道D_c,60达到0.46的水平，周向不均匀度达到5.2%的水平，影响发动机工作的风险较高。
- 内埋载荷分离 /
- 进气道流场 /
- 嵌套网格 /
- 气动干扰 /
- 总压畸变
Abstract:
In response to the problem of embedded payload separation by using integrative computation of internal and external flows in the front end of the intake duct due to engineering constraints, a computational aerodynamics coupled six degree of freedom motion model, dynamic nested mesh, and internal and external flow coupling calculation strategy were used to conduct numerical simulation research on the unsteady flow field of payload separation by using integrative computation of internal and external flows. The characteristics of payload separation motion under the condition of integrated internal and external flow coupling and its impact on the flow field of the internal flow intake duct were analyzed and evaluated. The results showed that, considering the safety of payload separation and its impact on the intake flow field, the dispersed deployment scheme was relatively stable; the two-point symmetrical placement scheme resulted in the intake duct D_c,60 reaching a level of 0.46 and the circumferential distortion intensity reaching a level of 5.2%, which posed a higher risk of affecting engine operation.
- embedded payload separation /
- air intake flow field /
- overset mesh /
- aerodynamic interference /
- total pressure distortion

HTML

图 1 CFD-6DOF耦合求解流程图

Figure 1. CFD-6DOF coupled solution flowchart

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图 2 Sajben管道的几何形状与网格

Figure 2. Geometric shape and mesh of Sajben pipeline

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图 3 管道壁面压力系数及不同截面速度对比

Figure 3. Comparison of pipeline wall pressure coefficient and different cross-sectional velocities

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图 4 机翼-挂架-载荷模型及流场计算网格

Figure 4. Wing-pylon-payload model and flow field calculation mesh

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图 5 载荷投放分离过程轨迹及表面压力系数分布云图

Figure 5. Cloud chart of trajectory and surface pressure coefficient distribution during the separation process of loading placement

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图 6 载荷重心位置和姿态的变化历程对比

Figure 6. Comparison of the change history of payload center of gravity position and attitude

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图 7 飞行器概念方案

Figure 7. Aircraft conceptual plan

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图 8 顺序分散投放方案

Figure 8. Sequential dispersed delivery plan

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图 9 两点对称投放方案

Figure 9. Two part symmetrical advertising plan

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图 10 载荷投放分离流程示意图

Figure 10. Schematic diagram of payload deployment separation process

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图 11 内外流一体建模示意图

Figure 11. Schematic diagram of integrated modeling of internal and external flow

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图 12 位置5示意图

Figure 12. Schematic diagram of position 5

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图 13 位置5投放过程进气道流场参数变化

Figure 13. Changes in intake flow field parameters during the placement process at position 5

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图 14 各位置投放过程进气道流场参数变化

Figure 14. Changes in intake flow field parameters during the placement process at different positions

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图 15 靠后位置示意图

Figure 15. Schematic diagram of the rear position

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图 16 靠后位置投放过程进气道流场参数变化

Figure 16. Changes in flow field parameters of the intake duct during the process of placing in the rear position

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图 17 前后位置投放过程进气道流场参数变化

Figure 17. Changes in intake flow field parameters during the process of front and rear placement

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表 1 3套不同密度网格流场数据对比

Table 1. Comparison of three sets of grid flow field data with different densities

疏密程度	网格数/10⁴	C_L	C_D	σ	D_c,60
粗	512	0.0715	0.0194	0.9521	0.2168
中	1102	0.0651	0.0176	0.9643	0.1921
细	1589	0.0657	0.0171	0.9655	0.1932

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表 2 各位置进气道气动参数对比

Table 2. Comparison of aerodynamic parameters of intake ducts at different positions

位置	σ_min	D_c,60,max	$ \Delta {\overline{\sigma }}_{0,\mathrm{max}} $/%
1	0.9277	0.4393	4.2834
2	0.9370	0.4401	4.2276
3	0.9396	0.4211	4.1858
4	0.9288	0.4213	4.1604
5	0.9211	0.4203	4.3162
6	0.9172	0.3872	4.3354

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表 3 前后位置进气道气动参数对比

Table 3. Comparison of aerodynamic parameters of front and rear intake ducts

位置	σ_min	D_c,60,max	$ \Delta {\overline{\sigma }}_{0,\mathrm{max}} $/%
靠后位置	0.8853	0.4575	5.1856
靠前位置	0.8842	0.4547	3.9854

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表 4 两种投放方案进气道气动参数值对比

Table 4. Comparison of aerodynamic parameter values for the intake duct of two deployment schemes

投放方案	σ_min	D_c,60,max	$ \Delta {\overline{\sigma }}_{0,\mathrm{max}} $/%
顺序分散	0.9172	0.4401	4.3354
两点对称	0.8842	0.4575	5.1856

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