基于流固耦合联合仿真的软管锥套式空中加油对接过程建模与分析

杨宇宸; 杨超越; 王斌; 索涛; 豆清波

doi:10.11883/bzycj-2024-0363

基于流固耦合联合仿真的软管锥套式空中加油对接过程建模与分析

doi: 10.11883/bzycj-2024-0363

杨宇宸^{1, 2},
杨超越^{1, 4},
王斌³,
索涛^{1, 4},
豆清波^{1, 4}

1.
西北工业大学航空学院，陕西西安 710072
2.
中国航空工业集团公司成都飞机设计研究所，四川成都 610073
3.
航空工业第一飞机设计研究院强度设计研究所，陕西西安 710089
4.
强度与结构完整性全国重点实验室，陕西西安 710072

详细信息

作者简介:
杨宇宸

中图分类号: O351.2; V212.1
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- 被引次数: 0
出版历程
- 网络出版日期: 2025-03-04

Modeling and analysis of hose-drogue aerial refueling docking process based on fluid-solid coupling simulation

YANG Yuchen^{1, 2},
YANG Chaoyue^{1, 4},
WANG Bin³,
SUO Tao^{1, 4},
DOU Qingbo^{1, 4}

1.
School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, Shaanxi, China
2.
AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610073, Sichuan, China
3.
Strength Design Institute, AVIC the First Aircraft Institute, Xi’an 710089, Shaanxi, China
4.
National Key Laboratory of Strength and Structural Integrity, Xi’an 710072, Shaanxi, China

摘要

摘要: 软管锥套式空中加油过程涉及气动力、燃油流动、柔性结构变形的复杂耦合，其耦合求解对仿真技术要求高、计算量大，严重制约了软管空中加油的准确性与安全性。为了准确分析软管锥套组合体在对接输油过程中的动力学特性，避开动力学方程建模的劣势，提出了一种考虑气动力、尾涡、软管变形与气流场双向影响、燃油内部流动综合影响下软管锥套组合体结构变形过程的流固耦合有限元模型及求解方法。模型中计算了稳定伞的作用效果并等效解耦成力和转角边界条件，推导了机翼尾涡作用力方程，采用联合仿真技术进行了流固耦合分析，软管拖曳平衡状态的计算结果与试验数据吻合良好。通过进一步仿真计算，对燃油流动、对接参数及飞行参数等甩鞭现象产生的影响因素进行了分析，结果表明：对接速度和回收加速度的匹配关系是甩鞭载荷的主要影响因素，回收加速度与最优匹配对接速度大小正相关；其次，飞行参数是次要影响因素，在不考虑燃油流动时，每一种高度下都呈现出“飞行速度越高，甩鞭载荷越低”的特点；燃油流动是一项干扰因素，一定程度会干扰上述规律，但不会影响整体规律，需要针对工况进行分析。
- 空中加油 /
- 软管锥套组合体 /
- 流固耦合 /
- 联合仿真 /
- 影响因素
Abstract: The hose-drogue aerial refueling process involves the complex coupling of aerodynamic force, fuel flow, and flexible structure deformation. Solving these interactions requires advanced simulation techniques and significant computational resources, which posed challenges to the accuracy and safety of practical implementations. A novel fluid-solid coupling model and methodology integrating aerodynamic loads, wake vortex effects, hose flexibility, airflow and internal fuel flow were developed to analyze structural deformation of hose-drogue assembly during docking and fuel transfer phases, overcoming limitations of traditional kinetic equation modeling. The aerodynamic forces of the paradrogue were obtained by performing separate CFD modeling on the paradrogue and conducting steady-state calculations. Meanwhile, the stabilizing moment of the paradrogue was equivalently converted into the lateral and rotational boundary condition at the center point of the paradrogue. Subsequently, based on the Hallock-Burnham model, the analytical expressions of the aerodynamic loads on the hose-drogue assembly under the action of the wake vortex alone were derived, and the aerodynamic loads were applied to hose-drogue assembly by ABAQUS subroutine. With the proposed model, the multi-stage operational processes of hose-drogue aerial refueling including steady-state, docking-state and refueling-state were calculated. Fluid-solid coupling simulations, which were conducted through Co-simulation, demonstrated excellent agreement with experimental data, particularly under the steady-state. Furthermore, the influence of fuel flow characteristics, docking parameters and flight parameters were systematically identified. The results show that the matching relationship between the docking speed and retracting acceleration is the main influencing factor of whiplash load, and the retracting acceleration is positively correlated with the magnitude of the optimally matched docking velocity. In addition, the flight parameters are the secondary influencing factors. When the fuel flow is not considered, it is established at each altitude that the higher the flight speed, the lower the whiplash load. Fuel flow dynamics acts as a disturbing factor that partially perturbs the established relationship between whiplash loads and key operational parameters. However, these disturbances do not fundamentally alter the overall trend, and therefore, analyses under specific conditions are imperative to account for the effects of the fuel flow in different situations.
- air refueling /
- hose-drogue assembly /
- fluid-solid coupling /
- co-simulation /
- influencing factors

HTML全文

图 1 HDA动力学模型^[5]

Figure 1. Dynamic Modeling of HDA^[5]

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图 2 卷盘与软管锥套组合体^[21]

Figure 2. Hose-drum and HDA^[21]

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图 3 HDA的载荷与边界条件

Figure 3. Force and boundary conditions of HDA in different states

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图 4 CFD求解稳定伞气动力

Figure 4. Calculation of aerodynamic force of para-drogue

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图 5 吊舱与回收绞盘建模

Figure 5. Modeling of refueling pod and HDA

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图 6 仿真模型总体图

Figure 6. General view of the simulation model

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图 7 加油机尾涡

Figure 7. Wake vortex of tanker

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图 8 速度分量与HDA形状

Figure 8. Velocity components and shape of HDA

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图 9 拖曳平衡状态结构变形

Figure 9. Deformation of HDA (steady-state)

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图 10 试验数据与模型仿真结果对比

Figure 10. Comparison of test data and simulation result

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图 11 气流场网格无关性

Figure 11. Grid independence of air flow field

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图 12 液流场网格无关性

Figure 12. Grid independence of liquid flow field

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图 13 HDA结构变形

Figure 13. Deformation of HDA

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图 14 简单弯曲管道内流

Figure 14. Flow in a simple curved pipe

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图 15 简单弯管的回收平复震荡过程

Figure 15. Deformation trend of simple bends at different moments

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图 16 HDA弯曲段形状

Figure 16. Shape of HDA curved segment

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图 17 锥套${a_{\textit{z}}}$历程（${v_{{\text{dock}}}}$=1.0～1.4 m/s,${a_{{\text{retract}}}}$=4 m/s²）

Figure 17. ${a_{\textit{z}}}$curve of para-drogue (${v_{{\text{dock}}}}$=1.0～1.4 m/s ${a_{{\text{retract}}}}$=4 m/s²)

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图 18 锥套${a_{\textit{z}}}$历程（${v_{{\text{dock}}}}$=1.5～1.8 m/s,${a_{{\text{retract}}}}$=4 m/s²）

Figure 18. ${a_{\textit{z}}}$curve of para-drogue (${v_{{\text{dock}}}}$=1.5～1.8 m/s, ${a_{{\text{retract}}}}$=4 m/s²)

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图 19 锥套${a_{{\textit{z}},\max }}$-${v_{{\text{dock}}}}$曲线(${a_{{\text{retract}}}}$=4 m/s²)

Figure 19. ${a_{{\textit{z}},\max }}$-${v_{{\text{dock}}}}$curve of para-drogue (${a_{{\text{retract}}}}$=4 m/s²)

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图 20 锥套${a_{{\textit{z}},\max }}$-${v_{{\text{dock}}}}$曲线

Figure 20. ${a_{{\textit{z}},\max }}$-${v_{{\text{dock}}}}$curve of para-drogue

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图 21 不同飞行参数下HDA锥套对接峰值加速度

Figure 21. Peak acceleration for different flight parameters

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图 22 不同参数组合下HDA锥套对接峰值加速度

Figure 22. Peak acceleration of paradrogue for different parameter combinations

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表 1 软管锥套组合体材料参数^[26]

Table 1. Parameters of HDA^[26]

参数长度/
m 弹性模量/
MPa 线密度/
(kg·m⁻¹) 泊松比锥套质量/
kg

23.9 300 7.73 0.4 39

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表 2 拖曳平衡验证所用空中加油参数^[21]

Table 2. Air refueling parameters used for Steady-State^[21]

参数飞行高度/
m 飞行速度/
(m·s⁻¹) 加油泵压/
MPa 加油流量/
(L·min⁻¹)

7000 220 0.345 1500

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