直升机CFD仿真现状与发展趋势分析

肖中云; 郭永恒; 张露; 崔兴达

doi:10.7638/kqdlxxb-2020.0067

直升机CFD仿真现状与发展趋势分析

doi: 10.7638/kqdlxxb-2020.0067

中国空气动力研究与发展中心计算空气动力研究所，绵阳　621000

基金项目: 国家数值风洞工程（NNW）

详细信息

作者简介:
肖中云（1977-），男，四川大竹人，研究员，研究方向：计算空气动力学. E-mail：scxiaozy@sina.cn

通讯作者:
郭永恒^*，助理研究员，研究方向：计算空气动力学. E-mail：matrixspace@163.com

中图分类号: V211.3; V212.4
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- 被引次数: 0
出版历程
- 收稿日期: 2020-04-21
- 修回日期: 2020-07-20
- 录用日期: 2020-07-22
- 网络出版日期: 2020-09-10
- 刊出日期: 2021-08-25

An analysis of current status and prospects of CFD based simulation of rotorcrafts

Computational Aerodynamics Institute of China Aerodynamics Research and Development Center, Mianyang　621000, China

摘要

摘要: 传统直升机气动设计较多依赖升力线理论、涡流理论等工程分析方法，高性能计算使采用CFD方法开展“第一性原理”仿真成为可能。本文从旋翼运动特点出发介绍了直升机区别于固定翼飞机的一些特殊计算方法，指出当前CFD方法在直升机实际应用中存在的不足。在此基础上，探讨了国外先进直升机CFD软件的发展策略与技术途径，从多求解器耦合、网格动态自适应技术、高阶格式与湍流模型的选取、多学科耦合求解等四个方面分析了这些软件的特点与技术优势。最后就如何适应未来发展需要，提出了直升机CFD能力建设方面的几点建议。分析表明，直升机由于旋翼运动具有与操纵输入、结构变形相耦合的特点，分部件及单学科的CFD分析方法与真实飞行状态存在偏差，多学科耦合分析与旋翼尾迹的精细模拟应当是软件未来发展的重点。
- 直升机 /
- 多学科 /
- 仿真 /
- 并行 /
- 航空力学
Abstract: Traditionally, the aerodynamic design of rotorcrafts relies heavily on engineering analysis methods such as lift line or vortex theory. Nowadays, however, high-performance computing makes the high-fidelity first principle simulation possible by computational fluid dynamics (CFD) methods. Based on the characteristics of rotor motions, some particular CFD methods are introduced and compared with those for fixed wings, and the shortcomings of current CFD in engineering applications are pointed out. On this basis, the development strategies and technical routines of foreign advanced helicopter CFD softwares are discussed, whose numerical methods and related technique merits are analyzed from multiple aspects including multi-solver coupling, dynamically adaptive mesh refinement, high-order schemes, turbulence models, and multi-disciplinary coupling analyses. Lastly, some suggestions on rotorcraft simulations are put forward to satisfy future needs. Due to the coupling between rotor motions and control inputs as well as structural deformations, results of CFD simulations in the way of part-by-part analyses or single-disciplinary modeling deviate from actual flight states. Therefore, future softwares of rotorcrafts should focus on multi-disciplinary coupled solutions and high resolution of rotor wakes.
- rotorcraft /
- multi-disciplinary /
- simulation /
- parallel /
- aeromechanics

HTML全文

图 1 VTM模拟得到的旋涡尾迹^[25]

Figure 1. Vortex wakes obtained by a simulation based on the vortex transport model^[25]

下载: 全尺寸图片幻灯片

图 2 模拟旋翼的双网格计算模式

Figure 2. Dual-mesh paradigm for rotor simulation

下载: 全尺寸图片幻灯片

图 3 Helios软件集成框架^[40]

Figure 3. The integration framework of Helios^[40]

下载: 全尺寸图片幻灯片

图 4 单元AMR与SAMR比较^[69]

Figure 4. A comparison between the (left) cell-based and the (right) block structured AMR^[69]

下载: 全尺寸图片幻灯片

图 5 H145直升机下降飞行的涡量等值面图^[100]

Figure 5. The vorticity iso-surface around a descending H145^[100]

下载: 全尺寸图片幻灯片

表 1 国外直升机CFD软件一览表

Table 1. A list of foreign rotorcraft CFD solvers

软件名称	机构	网格类型	尾迹模拟
GT-Hybrid	Geogia大学	结构网格	自由尾迹
Overturns	Maryland大学	结构网格	涡追踪网格
HMB	Glasgow大学	结构网格	直接模拟
U²NCLE	Toledo大学	非结构网格	直接模拟
ElsA	ONERA	结构/非结构	直接模拟
Overflow-D	NASA	结构网格	直接模拟
Helios	CREAT AV	混合网格	直接模拟

下载: 导出CSV

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