• 论文 •

### 基于CFD/CSD松耦合的直升机配平分析方法

1. 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
• 收稿日期:2019-06-25 发布日期:2020-05-19
• 通讯作者: 刘勇 E-mail:liuyong@nuaa.edu.cn
• 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。
• 基金资助:
江苏高校优势学科建设工程

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

YU Jin, WANG Song, LIU Yong, YANG Weidong

1. National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China
• Received:2019-06-25 Published:2020-05-19

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.