前体尾流对降落伞工作性能的影响

吴卓恒; 余莉; 赵晓舜; 聂舜臣

doi:10.13700/j.bh.1001-5965.2020.0465

前体尾流对降落伞工作性能的影响

doi: 10.13700/j.bh.1001-5965.2020.0465

吴卓恒¹,
余莉^{1, 2, ,},
赵晓舜¹,
聂舜臣¹

1.
南京航空航天大学飞行器环境控制与生命保障工业和信息化部实验室, 南京 210016
2.
南京航空航天大学航空学院, 南京 210016

基金项目:

国家自然科学基金 11972192

详细信息

通讯作者:
余莉, E-mail: yuli_happy@nuaa.edu.cn

中图分类号: V244.21
计量
- 文章访问数: 235
- HTML全文浏览量: 26
- PDF下载量: 24
- 被引次数: 0
出版历程
- 收稿日期: 2020-08-26
- 录用日期: 2020-11-06
- 网络出版日期: 2021-12-20

Effects of capsule wake on parachute working performance

1.
Key Laboratory of Aircraft Enviroment Control and Life Support, MIIT, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
2.
College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Funds:

National Natural Science Foundation of China 11972192

More Information

Corresponding author: YU Li, E-mail: yuli_happy@nuaa.edu.cn

摘要

摘要:
为研究前体尾流对降落伞工作性能的非定常影响，基于Realizablek-ε湍流模型采用PISO算法开展了物伞系统的非定常绕流数值计算，获得了精细的流场旋涡结构。在此基础上，研究了不同拖曳比下物伞系统的尾涡演变规律、流场分布规律以及伞衣气动特性变化。结果表明：前体尾涡导致伞衣入口处的涡量大小和方向时刻变化，随拖曳比增加，涡量黏性耗散增强，进入伞衣的旋涡强度逐渐减弱，伞衣入口形成稳定的负涡量区，伞衣尾涡脱离周期随之延长；拖曳比对尾涡区后端（伞衣入口处）流场压力的影响远大于前端，随拖曳比增加，流动形式逐渐由闭式转变为开式，流场的速度分布和压力分布更为对称，伞衣入口形成稳定的正压区，内外压差增加；当拖曳比大于9时，前体尾流对降落伞阻力系数和表面压强系数的影响减小。
- 前体尾流 /
- 降落伞 /
- 流场分布 /
- 尾涡演变 /
- 气动特性
Abstract:
To study the unsteady effects of capsule wake on parachute aerodynamic performance, the Realizable k-ε turbulence model and PISO algorithm are used to calculate the unsteady flow around the capsule-parachute system, and an accurate flow field vortex structure is obtained. The research on the variation of vortex, the flow field distribution and the aerodynamic characteristics of the canopy at different trailing distances has been carried out. The results show that the vortex of capsule wake causes the magnitude and direction of the vorticity at the entrance of the canopy to change constantly. As the trailing distance increases, the vorticity magnitude gradually decreases because of the increase of the vorticity's viscous dissipation, and a stable negative vortex area is formed at the entrance of the canopy. The canopy vortex's escape period is extended. The trailing distance has a much greater influence on the flow field pressure at the entrance of the canopy than at capsule. As this distance increases, the flow form gradually changes from closed to open, the velocity and pressure distribution of the flow field become more symmetrical, and a stable positive pressure zone is formed. The internal and external pressure difference increases. The influence of the capsule wake on the drag coefficient and surface pressure coefficient of the canopy is reduced when drag ratio equals or greater than 9.
- capsule wake /
- parachute /
- flow field distribution /
- variation of wake vortex /
- aerodynamic characteristics

HTML全文

图 1 伞衣平面结构参数^[18]

Figure 1. Planar structure parameters of canopy^[18]

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图 2 伞衣充满外形和计算网格

Figure 2. Full shape of canopy and computational grid

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图 3 降落伞尾涡结构

Figure 3. Parachute wake vortex structure

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图 4 物伞系统三维模型

Figure 4. 3-D model of capsule-parachute system

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图 5 物伞系统数值模型

Figure 5. Numerical model of capsule-parachute system

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图 6 流场旋涡演变规律

Figure 6. Variation rule of flow field vortex

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图 7 物伞尾涡脱离周期和平均涡核涡量

Figure 7. Wake vortex departure period and average vorticity magnitude of capsule-parachute system

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图 8 伞衣入口处旋涡强度变化

Figure 8. Variation of vorticity magnitude at the entrance of canopy

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图 9 物伞系统流场图(t=15 s)

Figure 9. Flow field of capsule-parachute system(t=15 s)

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图 10 流场压力变化

Figure 10. Variation of flow field pressure

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图 11 伞衣沿子午线上的内外压力及压强系数分布

Figure 11. Internal and external pressure and pressure intensity coefficient distribution along the meridian of canopy

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图 12 阻力系数随时间的变化

Figure 12. Variation of drag coefficient with time

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图 13 平均阻力系数随拖曳比的变化

Figure 13. Variation of average drag coefficient with drag ratio

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表 1 数值计算结果

Table 1. Numerical calculation results

湍流模型	平均阻力系数C_D	物理时长/s	计算时长/h	试验相对误差/%
Standard k-ε	0.732	8	5	-10.73
Realizable k-ε	0.781	8	8.5	-4.76

下载: 导出CSV

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