前行桨叶概念旋翼动力学分析方法

陈全龙; 韩景龙; 员海玮

doi:10.7527/S1000-6893.2014.0075

航空学报 >

2014 , Vol. 35 >Issue 9: 2451 - 2460

DOI: https://doi.org/10.7527/S1000-6893.2014.0075

流体力学与飞行力学

前行桨叶概念旋翼动力学分析方法

陈全龙 ,
韩景龙 ,
员海玮

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1. 中国直升机设计研究所旋翼动力学重点实验室, 江西景德镇 333000;
2. 南京航空航天大学机械结构力学与控制国家重点实验室, 江苏南京 210016

陈全龙男，博士，工程师。主要研究方向：旋翼动力学，直升机全机动力学。Tel：0798-8465751 E-mail：cql_nuaa@163.com；韩景龙男，博士，教授，博士生导师。主要研究方向：飞行器气动弹性力学，旋翼动力学。Tel：025-84896484 E-mail：hjlae@nuaa.edu.cn；员海玮男，博士，副教授。主要研究方向：飞行器气动弹性力学，飞行颤振试验。Tel：025-84896484 E-mail：yhwae@nuaa.edu.cn

收稿日期: 2013-11-22

修回日期: 2014-04-24

网络出版日期: 2014-05-23

基金资助

国家自然科学基金（11102085）；国家“863”计划（2012AA112201）

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Analytical Method for Advancing Blade Concept Rotor Dynamics

CHEN Quanlong ,
HAN Jinglong ,
YUN Haiwei

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1. Science and Technology on Rotorcraft Aeromechanics Laboratory, China Helicopter Research and Development Institute, Jingdezhen 333000, China;
2. State Key Laboratory of Mechanics and Control for Mechanical Structures, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received date: 2013-11-22

Revised date: 2014-04-24

Online published: 2014-05-23

Supported by

National Natural Science Foundation of China (11102085); National High-tech Research and Development Program of China (2012AA112201)

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摘要

根据前行桨叶概念（ABC）旋翼配平方程中未知量多于方程数的特点，提出了一种基于优化的配平问题求解方法。进而结合计算流体力学（CFD）/计算结构动力学（CSD）松耦合策略，建立了ABC旋翼动力学分析方法。CFD分析中以非定常Euler/Navier-Stokes方程为控制方程，通过动态重叠网格及动网格方法实现桨叶的运动及变形；桨叶结构模型采用非线性中等变形梁理论建立。以XH-59A直升机为例，对不同前飞速度下的旋翼效率进行了仿真分析，计算结果与飞行试验值吻合良好。仿真结果表明，该旋翼动力学分析方法具有很好的分析精度和收敛性，可广泛应用于ABC旋翼动力学分析。

关键词： 前行桨叶概念; CFD/CSD耦合; 旋翼动力学; 气动弹性; 直升机

本文引用格式

陈全龙 , 韩景龙 , 员海玮 . 前行桨叶概念旋翼动力学分析方法[J]. 航空学报, 2014 , 35(9) : 2451 -2460 . DOI: 10.7527/S1000-6893.2014.0075

Abstract

For advancing blade concept(ABC) rotors, the number of unknowns is more than the number of trimming equations. To obtain a reasonable solution, a trim analysis method based on optimization process is presented. Then a dynamic analysis method for ABC rotors is developed based on computational fluid dynamics(CFD)/computational structural dynamics(CSD) coupling technique. In CFD analysis, the governing equations, i.e., Euler/Navier-Stoke equations are solved and the overset grid and dynamic grid techniques are employed to simulate the blade motion and deformation; while the structure model of blades is established by moderate deflection beam theory. The XH-59A helicopter is taken as an example. The aerodynamic performances at different airspeeds have been investigated and the results fit well with the flight test data. The results demonstrate the accuracy and convergence of the presented method and also show its capability for potential application in ABC rotor dynamic analysis.

Key words： advancing blade concept; CFD/CSD coupling; rotor dynamics; aeroelasticity; helicopter

参考文献

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