基于升力面自由尾迹的直升机旋翼悬停性能参数影响研究

doi:CNKI:11-1929/V.20111031.1056.003

流体力学与飞行力学

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基于升力面自由尾迹的直升机旋翼悬停性能参数影响研究

谭剑锋¹, 王浩文¹, 林长亮²

1. 清华大学航天航空学院, 北京 100084;
2. 南京航空航天大学航空宇航学院, 江苏南京 210016

收稿日期:2011-05-27 修回日期:2011-07-11 出版日期:2012-02-25 发布日期:2012-02-24
通讯作者: 王浩文 E-mail:bobwang@mail.tsinghua.edu.cn
作者简介:谭剑锋男,博士研究生.主要研究方向:旋翼动力学和总体设计. Tel: 010-51537573 E-mail: windtam2003@yahoo.com.cn
王浩文男,博士,教授,博士生导师.主要研究方向:旋翼动力学、直升机结构强度及振动载荷分析. Tel: 010-62792661 E-mail: bobwang@mail.tsinghua.edu.cn
林长亮男,博士研究生.主要研究方向:直升机动力学. Tel: 025-84890690 E-mail: lclnuaa@yahoo.com.cn

Analysis of Influence of Rotor Parameters on Rotor Hover Performance by Lifting-Surface and Free Wake Method

TAN Jianfeng¹, WANG Haowen¹, LIN Changliang²

1. School of Aerospace, Tsinghua University, Beijing 100084, China;
2. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China

Received:2011-05-27 Revised:2011-07-11 Online:2012-02-25 Published:2012-02-24

摘要/Abstract

摘要： 最大悬停效率(FM_max)作为衡量旋翼悬停性能的常用指标,反映了旋翼能达到的最大悬停效率,但不能反映旋翼在一定桨叶载荷范围内保持高悬停效率的能力,本文给出了旋翼悬停保持能力的定义.为更准确地反映桨叶涡量分布,建立了基于升力面理论的桨叶气动模型;考虑有弯度翼型的影响,将涡量布置于翼型中弧线,随后基于自由尾迹模型、耦合刚性桨叶挥舞运动方程、翼型动态失速模型以及二阶精度时间步进格式建立了升力面自由尾迹方法.通过计算模型旋翼在不同桨尖马赫数下的悬停效率,并与试验数据对比,验证了方法的准确性.相比于升力线自由尾迹方法,建立的升力面自由尾迹分析方法能显著提高旋翼悬停效率计算精度.最后分析旋翼关键设计参数对悬停性能的影响,得到设计参数影响旋翼悬停保持能力的新规律.

关键词: 自由尾迹, 升力面, 旋翼, 悬停性能, 悬停保持能力

Abstract: The maximum figure of Merit (FM_max) is the most important index for a rotor which indicates the greatest hover efficiency the rotor can achieve. However, it cannot reflect the rotor's ability to keep a high Figure of Merit (FM) in certain blade load ranges. Therefore a new concept, the hover hold ability (HHA) of roltor is defined in this paper. In order to describe the distribution of vortices on a blade more accurately, the lifting-surface is used in the blade aerodynamic model. To take into consideration different airfoils, vortices of a blade are set on the middle line of an airfoil. Based on the free-wake model, a calculation method of rotor performance is established which includes the lifting-surface model, rigid blade flap equation, airfoil dynamics stall model and second-order time accurate algorithm. The model rotor FM with different tip Mach numbers (Ma_tip) is calculated and compared with test results to validate the precision of the method. Compared with the free-wake model which includes a lifting-line model, more accurate FM of rotor is attained. Finally, the influence of critical rotor design parameters on rotor hover performance is analyzed, and new laws for the effect of design parameters on rotor hover hold ability are obtained.

Key words: free wake, lifting-surface, rotors, hover performance, hover hold ability

中图分类号:

V211.52

谭剑锋, 王浩文, 林长亮. 基于升力面自由尾迹的直升机旋翼悬停性能参数影响研究[J]. 航空学报, 2012, 33(2): 249-257.

TAN Jianfeng, WANG Haowen, LIN Changliang. Analysis of Influence of Rotor Parameters on Rotor Hover Performance by Lifting-Surface and Free Wake Method[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2012, 33(2): 249-257.

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E-mail：hkxb@buaa.edu.cn

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主管单位：中国科学技术协会主办单位：中国航空学会北京航空航天大学

基于升力面自由尾迹的直升机旋翼悬停性能参数影响研究

Analysis of Influence of Rotor Parameters on Rotor Hover Performance by Lifting-Surface and Free Wake Method

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