Investigation of Rotor Dynamic Stability and Mutual Excitation of Different Degrees of Freedoms in Forward Flight

XUE Hai-feng; XIANG Jin-wu; ZHANG Xiao-gu

Chinese

您当前的位置：

首页 >

文章列表页 >

Investigation of Rotor Dynamic Stability and Mutual Excitation of Different Degrees of Freedoms in Forward Flight

更新时间：2026-07-07

- Investigation of Rotor Dynamic Stability and Mutual Excitation of Different Degrees of Freedoms in Forward Flight
- Vol. 19, Issue 5, (2004)
- 作者机构：
  
  北京航空航天大学航空科学与工程学院,北京,100083
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2004
- 稿件说明：
移动端阅览
XUE Hai-feng, XIANG Jin-wu, ZHANG Xiao-gu. Investigation of Rotor Dynamic Stability and Mutual Excitation of Different Degrees of Freedoms in Forward Flight[J]. 2004, 19(5).
DOI：

XUE Hai-feng, XIANG Jin-wu, ZHANG Xiao-gu. Investigation of Rotor Dynamic Stability and Mutual Excitation of Different Degrees of Freedoms in Forward Flight[J]. 2004, 19(5). DOI：

摘要

为研究直升机在前飞状态下的稳定性

建立了前飞状态下旋翼的结构模型、气动力模型和平衡方程组。对方程组的周期系数处理以及前飞时的相关参数对旋翼动稳定性的影响等进行了研究。在前飞动稳定性分析中引入动力入流自由度。从分析各个自由度间的相互作用入手揭示旋翼动不稳定性的物理本质及影响因素。

Abstract

It is more difficult to investigate the helicopter dynamic stability in forward flight than in hover.The rotor structure model

aerodynamic model and equations of motion were established.The treatment of equations with periodic coefficients and the influence of related parameters on rotor dynamic stability were investigated.The degree of freedom of the dynamic inflow was introduced into the dynamic stability analysis in forward flight.Starting with the analysis of mutual excitation of different degrees of freedom

the physical nature and influence factors on rotor dynamic instability are revealed.

关键词

Keywords

references

Views

447

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Study of aerodynamic model for the maneuvering rotor

Numerical Simulations for the Flowfield of Helicopter Rotors in Hovering Based on High-Order Upwind Flux-Difference Splitting Scheme

Numerical Simulation of Airfoil-Tip Vortex Interaction

Method on helicopter BVI noise reduction based onmiss-distance control

Analysis on three-dimensional effects of rotor unsteady dynamic stall

Related Author

XU Jin

GAO Zheng

ZHAO Qi-jun

XU Guo-hua

CAO Yi hua

KANG Peng bin

YU Zi wen

ZHANG Wei

Related Institution

Laboratory of Rotorcraft Aeromechanics, Nanjing University ofAeronautics and Astronautics

National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics

Beijing University of Aeronautics and Astronautics

National Laboratory of Science and Technology on Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics

China Helicopter Research and Development Institute, Aviation Industry Corporation of China, Limited

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰