北京航空航天大学学报 ›› 2018, Vol. 44 ›› Issue (1): 50-62.doi: 10.13700/j.bh.1001-5965.2017.0033

• 论文 • 上一篇    下一篇

共轴刚性双旋翼非定常气动干扰载荷分析

谭剑锋1, 孙义鸣1, 王浩文2, 林长亮3   

  1. 1. 南京工业大学 机械与动力工程学院, 南京 211816;
    2. 清华大学 航天航空学院, 北京 100084;
    3. 航空工业哈尔滨飞机工业集团有限责任公司飞机设计研究所, 哈尔滨 150066
  • 收稿日期:2017-01-18 修回日期:2017-08-11 出版日期:2018-01-20 发布日期:2018-01-29
  • 通讯作者: 谭剑锋 E-mail:Jianfengtan@njtech.edu.cn
  • 作者简介:谭剑锋,男,博士,讲师。主要研究方向:旋翼空气动力学与结构动力学、风机空气动力学;孙义鸣,男,硕士研究生。主要研究方向:旋翼空气动力学、风机空气动力学;王浩文,男,博士,教授,博士生导师。主要研究方向:旋翼动力学、结构强度及振动载荷分析;林长亮,男,博士,高级工程师。主要研究方向:直升机气动设计、总体设计、旋翼结构动力学。
  • 基金资助:
    国家自然科学基金(11502105);江苏省自然科学基金(BK20161537);江苏省高校自然科学研究面上项目(15KJB130004)

Analysis of rigid coaxial rotor unsteady interactional aerodynamic loads

TAN Jianfeng1, SUN Yiming1, WANG Haowen2, LIN Changliang3   

  1. 1. School of Mechanical and Power Engineering, Nanjing Tech University, Nanjing 211816, China;
    2. School of Aerospace Engineering, Tsinghua University, Beijing 100084, China;
    3. Institute of Aircraft Design, AVIC Harbin Aircraft Industry Group Co., Ltd., Harbin 150066, China
  • Received:2017-01-18 Revised:2017-08-11 Online:2018-01-20 Published:2018-01-29

摘要: 共轴刚性双旋翼系统提高直升机最大前飞速度,但旋翼振动载荷明显增大。为研究高速共轴刚性双旋翼系统振动载荷特性,须首先分析共轴刚性双旋翼气动干扰下的非定常气动载荷。基于非定常面元法建立满足桨叶前缘和后缘边界条件的旋翼反流区气动模型以体现高速共轴刚性双旋翼后行边反流区影响,且增加共轴刚性双旋翼桨尖涡-桨叶气动干扰模型以体现共轴刚性双旋翼非定常气动干扰影响,并结合基于黏性涡粒子法的共轴刚性双旋翼尾迹模型,构建高速共轴刚性双旋翼气动干扰下的气动载荷分析方法。通过计算前飞状态下的X2共轴刚性双旋翼特征剖面非定常气动载荷时间历程,并与PRASADUM以及基于NASA OVERFLOW和CREATE AV Helios的CFD/CSD计算结果对比,验证本文共轴刚性双旋翼非定常气动载荷分析方法的有效性。相比于PRASADUM,本文分析更好地体现上、下旋翼在前行边和后行边非定常气动载荷的变化特性,并与CFD/CSD计算结果更吻合。分析X2上、下旋翼气动干扰对共轴刚性双旋翼桨叶非定常气动载荷的影响,以及单旋翼与共轴刚性双旋翼非定常气动载荷差异。分析表明,低速状态下的共轴刚性双旋翼非定常气动载荷受双旋翼桨尖涡干扰显著,而高速前飞状态受双旋翼桨叶干扰明显,且表现出桨叶片数整数倍的辐射状干扰特征。

关键词: 共轴刚性双旋翼, 非定常气动载荷, 反流区, 面元法, 黏性涡粒子法

Abstract: The maximum forward speed for helicopter increases by adopting rigid coaxial rotor system, while the vibration load in rotor system obviously increases. In order to analyze the vibration characteristics of high-speed rigid coaxial rotor system, it is necessary to investigate unsteady aerodynamic loads of rigid coaxial rotor with aerodynamic interaction. Therefore, a rotor reverse flow aerodynamic model is established based on an unsteady panel method through satisfying boundary conditions of blade leading-edge and trailing-edge to reflect the influence of the reverse flow on the retreating side of the high-speed coaxial rotor. Moreover, a rigid coaxial rotor tip-vortex-blade aerodynamic model is added to describe the influence of aerodynamic interaction between the coaxial rotors. Coupling those models with the wake model of coaxial rotor based on a viscous vortex particle method, an unsteady aerodynamic analysis method under aerodynamic interaction of high-speed rigid coaxial rotor is established. The aerodynamic load at characteristic span of X2 rigid coaxial rotor is simulated during forward flight, and compared with the results of PRASADUM and CFD/CSD based on NASA OVERFLOW and CREATE AV Helios to validate the effectiveness of the present unsteady aerodynamic analysis method. Compared to PRASADUM, the present method better describes the variation characteristics of unsteady airloads of the upper and lower rotors on the advancing and retreading sides, and the results agree better with the computational results of CFD/CSD. Finally, the influence of aerodynamic interaction between the X2 upper and lower rotors on the unsteady aerodynamic loads is analyzed, and the difference of unsteady aerodynamic load between the single rotor and coaxial rotor is also investigated. It is shown that the unsteady aerodynamic load of rigid coaxial rotor is affected obviously by the tip vortex of coaxial rotor at low speed, while it is influenced by coaxial rotor blade at high speed. The characteristic of aerodynamic load of coaxial rotor is radial distribution with number of blades at high speed.

Key words: rigid coaxial rotor, unsteady aerodynamic load, reverse flow, panel method, viscous vortex particle method

中图分类号: 


版权所有 © 《北京航空航天大学学报》编辑部
通讯地址:北京市海淀区学院路37号 北京航空航天大学学报编辑部 邮编:100191 E-mail:jbuaa@buaa.edu.cn
本系统由北京玛格泰克科技发展有限公司设计开发