Modeling study on tilt-rotor's aeroelastic stability in cruise flight

XUE Li-peng; ZHANG Cheng-lin

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Modeling study on tilt-rotor's aeroelastic stability in cruise flight

更新时间：2026-07-07

- Modeling study on tilt-rotor's aeroelastic stability in cruise flight
- Vol. 24, Issue 2, (2009)
- 作者机构：
  
  南京航空航天大学直升机旋翼动力学国家重点实验室,南京,210016
- 作者简介：
- 基金信息：
- DOI：
  CLC：
- Published：2009
- 稿件说明：
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XUE Li-peng, ZHANG Cheng-lin. Modeling study on tilt-rotor's aeroelastic stability in cruise flight[J]. 2009, 24(2).
DOI：

XUE Li-peng, ZHANG Cheng-lin. Modeling study on tilt-rotor's aeroelastic stability in cruise flight[J]. 2009, 24(2). DOI：

摘要

基于刚性桨叶、刚体短舱及弹性机翼的假设

计入桨叶的变距/挥舞/摆振结构耦合及变距与万向铰的耦合

分别在惯性系下采用牛顿法和有限元法建立了旋翼和机翼的动力学方程

通过桨毂与短舱/机翼系统之间的共有自由度将动力学方程耦合起来

得到了前飞状态下全铰接式倾转旋翼/短舱/机翼耦合系统气弹稳定性分析模型

气动模型采用改进的叶素-动量理论

计入了扰动引起的非定常气动力影响.通过算例验证了建模的正确性.

Abstract

It's assumed that the rotor blade and nacelle were of a rigid body and the wing was represented by an elastic beam

the blade pitch/flap/lag structural coupling and pitch/gimbal coupling were considered

and then

tilt-rotor/wing dynamic equations were founded on the inertial coordinate frame according to Newton's Second law and finite element method.These two dynamic equations were coupled through the common degrees of freedom between the rotor hub and the nacelle/wing system

and then the tilt-rotor/nacelle/wing coupled system aeroelastic stability model of a full-hinged tilt-rotor during cruise flight was acquired.The rotor aerodynamic model was based on the improved element-momentum theory

with consideration of the velocity's unsteady aerodynamic influence of perturbation parts.The calculation shows that the model is correct.

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