Mathematical model for calculating wing download of tiltrotor aircraft

CAO Yun-yun; CHEN Ren-liang

Chinese

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Mathematical model for calculating wing download of tiltrotor aircraft

更新时间：2026-07-07

- Mathematical model for calculating wing download of tiltrotor aircraft
- Vol. 26, Issue 2, (2011)
- 作者机构：
  
  南京航空航天大学航空宇航学院直升机旋翼动力学重点实验室,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2011
- 稿件说明：
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CAO Yun-yun, CHEN Ren-liang. Mathematical model for calculating wing download of tiltrotor aircraft[J]. 2011, 26(2).
DOI：

CAO Yun-yun, CHEN Ren-liang. Mathematical model for calculating wing download of tiltrotor aircraft[J]. 2011, 26(2). DOI：

摘要

针对倾转旋翼飞行器悬停和小速度前飞的直升机飞行模式下旋翼下洗流对机翼的气动干扰影响

建立了一个机翼向下载荷的计算模型.该模型中

最关键的是建立旋翼对机翼的气动干扰面积模型.此模型考虑了倾转旋翼飞行器几何尺寸条件、发动机短舱倾转角和飞行状态等参数.最后将此模型集成到XV-15倾转旋翼飞行器飞行动力学模型中

进行配平计算

配平结果表明该倾转旋翼飞行器旋翼对机翼气动干扰产生的向下载荷模型是合理和有效的

适用于倾转旋翼飞行器的飞行动力学研究.

Abstract

A mathematical model for calculating wing download of tiltrotor aircraft in helicopter mode

which covers hover and low-speed forward flight

was given according to the aerodynamic interaction effect of the rotor downwash flow on the wing.The rotor and wing interaction area model considered the tiltrotor aircraft geometry scale

the tilt angle of the nacelle and the flight condition as key elements.Then the model was integrated into the XV-15 tiltrotor aircraft flight dynamic model.The trim results show that the rotor and the wing interaction download model of tiltrotor aircraft is reasonable and effective.The wing download math model is suitable for tiltrotor aircraft flight dynamic mathematical model.

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Investigation of control strategy for quad⁃tilt⁃rotor aircraft in helicopter mode

Unsteady aerodynamic interactions of contra rotating propeller

Numerical simulation of flow field under coaxial rigid rotor/fuselage interaction

Unsteady flow field interaction of coaxial rotor

Application of unsteady preconditioning to aerodynamic interaction simulation of tiltrotor aircraft in hover

Related Author

Renliang CHEN

Zhiming YU

Pan ZHOU

YANG Xiao

WANG Xuechen

WANG Fengming

TANG Sijia

YAN Wenhui

Related Institution

National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics，College of Aerospace Engineering，Nanjing University of Aeronautics and Astronautics

Department of Precision Instruments, School of Mechanical Engineering, Tsinghua University

School of Mechanical and Materials Engineering, North China University of Technology

Huiyang Aviation Propeller Company Limited, Aviation Industry Corporation of China, Limited

The Advanced Aviation Power Innovation Institute

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