无人直升机系留气动载荷CFD计算分析

龙海斌; 吴裕平

doi:10.13700/j.bh.1001-5965.2020.0308

无人直升机系留气动载荷CFD计算分析

doi: 10.13700/j.bh.1001-5965.2020.0308

龙海斌,
吴裕平^,

中国直升机设计研究所总体气动部, 景德镇 333001

详细信息

通讯作者:
吴裕平, E-mail: 24556384@qq.com

中图分类号: V275⁺.1;TB126
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- 被引次数: 0
出版历程
- 收稿日期: 2020-07-01
- 录用日期: 2020-07-19
- 刊出日期: 2021-09-20

CFD calculation and analysis of unmanned helicopter tie-down aerodynamic load

LONG Haibin,
WU Yuping^,

General Configuration and Aerodynamic Design Department, China Helicopter Research and Development Institute, Jingdezhen 333001, China

More Information

Corresponding author: WU Yuping, E-mail: 24556384@qq.com

摘要

摘要:
系留气动载荷作为无人直升机系留装置的设计输入，通常以机身大风侧向角气动特性风洞试验数据为基础进行计算。采用CFD计算方法对某无人直升机算例样机的机身大风侧向角气动特性进行了计算，包括自由来流、停放在开阔地面和船艉甲板3个状态，以机身气动特性CFD计算结果为基础计算了其系留气动载荷。结果表明：无人直升机在开阔地面停放时的系留气动载荷与自由来流时基本一致。而受船体上层建筑的影响，停放在船艉甲板时的系留气动载荷与自由来流时有较大的差别，除部分风侧向角状态的偏航力矩之外，力和部分力矩的绝对值相对较小，部分风侧向角状态的力和力矩方向相反。研究结果可为选取无人直升机系留气动载荷计算方法和不同停放环境下的机身气动特性的CFD计算及风洞试验状态提供一定的参考。
- 无人直升机 /
- 系留 /
- 气动载荷 /
- 开阔地面 /
- 船艉甲板 /
- CFD
Abstract:
The tie-down aerodynamic load is used as the design input for the mooring device of the helicopter. In the past, it was usually calculated based on the wind tunnel test data of the large wind side angle aerodynamic characteristics of the fuselage. First, the CFD method was used to calculate the aerodynamic characteristics of the large wind side angle of an unmanned helicopter fuselage, including free flow, parking on the open ground and ship bow deck. Based on the CFD calculation results of the aerodynamic characteristics of the fuselage, the tie-down aerodynamic load was calculated. The results show that when the unmanned helicopter is parked on the open ground, the tie-down aerodynamic load is basically the same as that of the free flow. However, due to the influence of the ship's superstructure, the difference between the tie-down aerodynamic load when parked on ship bow deck and that of the free flow is large. The absolute values of force and part of the moment of force are relatively small, and the direction of the force and the moment of force are opposite in the case of some wind side angles. The research results can provide a certain reference for selecting the calculation method of helicopter tie-down aerodynamic load, the CFD calculation and the wind tunnel test status of the aerodynamic characteristics of the fuselage in different parking environments.
- unmanned helicopter /
- tie-down /
- aerodynamic load /
- open ground /
- ship bow deck /
- CFD

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图 1 风洞试验模型

Figure 1. Wind tunnel test model

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图 2 不同类型网格划分示意图

Figure 2. Schematic diagram of the generation of different types of grid

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图 3 系留气动载荷CFD计算值与风洞试验结果对比

Figure 3. Comparison of CFD calculated value of tie-down aerodynamic load and wind tunnel test result

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图 4 计算模型示意图

Figure 4. Schematic diagram of calculation model

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图 5 计算网格划分示意图

Figure 5. Schematic diagram of computational grid generation

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图 6 各方向力的对比

Figure 6. Comparison of forces in various directions

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图 7 各方向力矩的对比

Figure 7. Comparison of moments of force in various directions

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图 8 0°风侧向角时的流线分布图

Figure 8. Streamline distribution when wind side angle is 0°

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图 9 180°风侧向角时的流线分布图

Figure 9. Streamline distribution when wind side angle is 180°

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表 1 计算状态

Table 1. Calculation status

参数	范围
迎角	0°
风侧向角	0°~345°(间隔15°)

下载: 导出CSV

表 2 不同计算模型网格数量

Table 2. Number of grids in each calculation model

类型	四面体网格	多面体网格
自由来流	105.1×10⁴	34.5×10⁴
开阔地面	101.4×10⁴	35.2×10⁴
船艉甲板	178.9×10⁴	50.4×10⁴

下载: 导出CSV

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