基于CFD/CSD松耦合的直升机配平分析方法

余瑾; 王松; 刘勇; 杨卫东

doi:10.13700/j.bh.1001-5965.2019.0329

基于CFD/CSD松耦合的直升机配平分析方法

doi: 10.13700/j.bh.1001-5965.2019.0329

南京航空航天大学直升机旋翼动力学国家级重点实验室, 南京 210016

基金项目: 江苏高校优势学科建设工程

详细信息

作者简介:
余瑾男, 博士研究生。主要研究方向:直升机旋翼气动弹性力学

王松男, 硕士研究生。主要研究方向:直升机旋翼气动弹性力学

刘勇男, 博士, 讲师。主要研究方向:直升机旋翼气动弹性力学

杨卫东男, 博士, 教授。主要研究方向:直升机旋翼气动弹性力学

通讯作者:
刘勇, E-mail: liuyong@nuaa.edu.cn

中图分类号: V249.3
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出版历程
- 收稿日期: 2019-06-25
- 录用日期: 2019-09-20
- 网络出版日期: 2020-05-20

Trim analysis method of helicopter based on CFD/CSD loose coupling

National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Funds: Priority Academic Program Development of Jiangsu Higher Education Institutions

More Information

Corresponding author: LIU Yong, E-mail: liuyong@nuaa.edu.cn

摘要

摘要:
针对直升机配平问题，基于CFD/CSD松耦合策略建立了计入旋翼气弹效应的配平分析方法。旋翼桨叶CSD求解器与旋翼CFD求解器以桨叶弹性轴和变距轴线为媒介，通过线性插值方法交换气动载荷和响应数据。CFD模块和CSD模块在时域内推进，旋翼每旋转一圈交互一次数据，以CFD模块计算的气动力来修正配平计算中气弹分析的气动力输入，直到配平量和CFD气动力在迭代过程中不再变化，即得到耦合配平解。以SA349/2“小羚羊”直升机小速度前飞状态为算例，计算表明所提方法收敛迅速、稳定性良好，计算结果与飞行实测值的对比分析验证了方法的有效性，对桨叶气动力曲线及桨涡干扰等现象具有很好的捕捉能力。
- 直升机 /
- CFD/CSD松耦合 /
- 配平 /
- 气动载荷 /
- 运动嵌套网格 /
- 插值
Abstract:
In this paper, a helicopter trim calculation method based on the CFD/CSD loose coupling strategy is proposed. The CSD solver and rotor CFD solver use the blade elastic axis and pitch axis as media to exchange aerodynamic load and response data through linear interpolation method. In the coupling strategy of this paper, CFD and CSD solver operate in the time domain respectively, and exchange the data once per revolution. The aerodynamic force calculated by CFD solver is used to correct the aerodynamic input of aeroelastic analysis in trim calculation, until the trim parameters and CFD aerodynamic force no longer change in the iterative process, and the coupling trim solutions are obtained. In this paper, the SA349/2 helicopter is taken as an example to calculate the forward flight state. The results show that the coupling method in this paper converges rapidly and has good stability. The comparison between the calculation results and the measured flight values verifies the effectiveness of the proposed method, and it has a good ability to capture the aerodynamic curve of blade and the blade vortex distraction.
- helicopter /
- CFD/CSD loose coupling /
- trim /
- aerodynamic load /
- moving nested mesh /
- interpolation

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图 1 SA349/2旋翼桨叶贴体网格

Figure 1. Body-fitted grid of SA349/2 rotor blade

下载: 全尺寸图片幻灯片

图 2 SA349/2旋翼流场笛卡儿自动背景网格

Figure 2. Cartesian automatic background grid of SA349/2 rotor flow field

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图 3 适合前飞状态求解的笛卡儿自动背景网格剖面

Figure 3. Cartesian automatic background grid section for solving in forward flight status

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图 4 旋翼前飞状态笛卡儿背景网格自适应

Figure 4. Cartesian adaptive background grid of rotor for forward flight

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图 5 旋翼网格运动与变形

Figure 5. Motion and deformation of rotor grid

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图 6 桨叶弹性变形示意图

Figure 6. Schematic of blade elastic deformation

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图 7 CSD模块与CFD气动力耦合计算流程

Figure 7. Flowchart of CSD/CFD aerodynamic force coupling calculation

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图 8 旋翼配平及耦合策略内外两层循环流程

Figure 8. Circulation flowchart of inner and outer loop for rotor trim and coupling strategy

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图 9 SA349/2直升机桨叶负扭转对比

Figure 9. Comparison of blade twist of SA349/2 helicopter

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图 10 桨叶剖面配平历程

Figure 10. Blade section trimming process

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图 11 低速飞行状态桨叶剖面垂直力系数对比

Figure 11. Comparison of vertical force coefficient of blade section in low-speed forward flight

下载: 全尺寸图片幻灯片

图 12 低速飞行状态桨叶剖面垂直力、俯仰力矩和弦向力分布

Figure 12. Distribution of blade normal force、pitching moment and in-plane force coefficient in low-speed forward flight

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图 13 低速飞行状态桨叶剖面压力系数对比

Figure 13. Comparison of blade surface pressure coefficient in low-speed forward flight

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图 14 低速飞行状态笛卡儿自动背景网格自适应计算旋翼涡量等轴视图

Figure 14. Rotor vorticity isometric view of Cartesian automatic background grid in low-speed forward flight

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表 1 SA349/2旋翼桨叶贴体网格规模统计

Table 1. Numbers of body-fitted grid of SA349/2 rotor blade

部件	网格规模	网格数
桨叶	237×163×61	2356491
内侧帽子	153×75×61	699975
外侧帽子	157×81×61	775737

下载: 导出CSV

表 2 SA349/2直升机飞行状态2^[15]的配平解

Table 2. Trim solution of SA349/2 helicopter in flight status 2^[15] (°)

配平解	总距θ₀	横向周期变距θ_1c	纵向周期变距θ_1s	俯仰角ϑ	侧倾角γ
数值	4.3787	1.5380	-0.6303	-3.1291	2.8975

下载: 导出CSV

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