Quasi-steady aerodynamic model of tilt rotor based on optimization algorithm

WU Da-wei; LI Shu

Chinese

您当前的位置：

首页 >

文章列表页 >

Quasi-steady aerodynamic model of tilt rotor based on optimization algorithm

更新时间：2026-07-07

- Quasi-steady aerodynamic model of tilt rotor based on optimization algorithm
- Vol. 28, Issue 4, (2013)
- 作者机构：
  
  1. 北京航空航天大学航空科学与工程学院,北京,100191
  2. 中国商用飞机有限责任公司上海飞机设计研究院,上海,200232
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2013
- 稿件说明：
移动端阅览
WU Da-wei, LI Shu. Quasi-steady aerodynamic model of tilt rotor based on optimization algorithm[J]. 2013, 28(4).
DOI：

WU Da-wei, LI Shu. Quasi-steady aerodynamic model of tilt rotor based on optimization algorithm[J]. 2013, 28(4). DOI：

摘要

取消了传统直升机旋翼准定常气动模型中对飞行工况和桨叶形状的诸多假设和限制

建立了适合倾转旋翼特殊桨叶形状、桨毂构造以及飞行工况的准定常气动模型.桨叶气动载荷计算基于叶素理论进行数值积分

旋翼挥舞系数通过序列二次规划算法(SQP)进行数值优化求解

诱导速度分布采用Pitt-Peters动态入流模型的稳态形式.利用该方法计算了XV-15倾转旋翼机的旋翼在不同工况下的气动性能以及挥舞系数.计算结果与风洞实验数据吻合良好

误差在8%以内且计算效率高

单一工况求解耗时在5min以内

该方法可用于倾转旋翼机总体设计阶段的性能分析或建立其飞行动力学模型.

Abstract

There are many hypotheses and limitations about the flight condition and blade shape in the quasi-steady aerodynamic model of conventional helicopter rotor

and many of them were eliminated considering the special blade shape

hub structure and flight condition of tilt rotor.Aerodynamic loads were calculated through numerical integration based on the blade element theory

and flap coefficients of tilt rotor were solved through sequential quadratic programming (SQP) algorithm.Induced velocity distribution was adopted as the steady form of Pitt-Peters dynamic inflow model.The aerodynamic performance and flap coefficients of the rotor of XV-15 tilt rotor aircraft were predicted by this method.The theoretical results and wind tunnel tests data make good agreement with error less than 8% and this method has high calculation efficiency that one case can be solved within 5 minutes

therefore

this method is applicable for aerodynamic performance prediction in preliminary design of tilt rotor aircraft and suitable to set up its flight dynamics model.

关键词

Keywords

references

Views

1264

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Effects of porous media on rod⁃airfoil interaction noise

Experimental and numerical simulation on aerodynamic performance of large radius change to length ratio intermediate casing

Effect of tip injection on aerodynamic performance of squealer tip

Surface roughness flow control mechanism of highly⁃loaded axial compressor under low Reynolds number conditions

Impacts of non⁃axisymmetric stagger angle on performance of compressor rotor blade

Related Author

Chenghao YANG

Heying FENG

Yehui PENG

Nüzi BAO

Jianming LIU

Shengchun HAO

Hui WU

Zhan ZHAO

Related Institution

Hunan Provincial Key Laboratory of Health Maintenance for Mechanical Equipment， Hunan University of Science and Technology

School of Mathematics and Computational Science，Hunan University of Science and Technology

Shenyang Engine Research Institute，Aero Engine Corporation of China

National Key Laboratory of Science and Technology on Aero⁃Engine Aero⁃thermodynamics，School of Energy and Power Engineering，Beihang University

Research Institute of Aero⁃Engine，Beihang University

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