旋翼/机身非线性气弹耦合配平及稳定性分析

胡新宇; 韩景龙; 喻梅

doi:10.3879/j.issn.1000-0887.2010.02.011

旋翼/机身非线性气弹耦合配平及稳定性分析

doi: 10.3879/j.issn.1000-0887.2010.02.011

中国矿业大学理学院力学系,江苏徐州 221008;

基金项目: 国家自然科学基金资助项目(10872089)

详细信息

作者简介:
胡新宇(1977- ),男,江苏徐州人,讲师,硕士(联系人.E-mail:xyhu@cum.tedu.cn).

中图分类号: O343.5;V211.52
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- 被引次数: 0
出版历程
- 收稿日期: 1900-01-01
- 修回日期: 2010-01-03
- 刊出日期: 2010-02-15

Nonlinear Aeroelastic Coupled Trim and Stability Analysis of Rotor-Fuselage

Department of Engineering Mechanics, College of Sciences, China University of Mining and Technology, Xuzhou, Jiangsu 221008, P. R. China;
Institute of Vibration Engineering Research, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, P. R. China

摘要

摘要: 根据Hamilton原理，采用中等变形梁理论，将桨叶离散为15自由度梁单元，用准定常气动模型建立旋翼/刚性机身耦合的有限元非线性方程，用时间有限元法进行气弹耦合配平计算，得到桨叶和机身运动的周期解．在此基础上，引入Peters动态入流模型分析耦合系统的稳定性．并研制相应的计算程序，可用于桨叶响应、桨叶和桨毂载荷、旋翼操纵等方面的分析计算．算例分析结果与相关文献吻合较好，且同时满足桨叶响应和配平方程的收敛性要求．
- 非线性 /
- 气弹响应 /
- 旋翼/机身耦合 /
- 时间有限元法 /
- 稳定性
Abstract: Based on the principle of Hamilton and the moderate deflection beam theory,discretizing the blade into a number of beame lements which had 15 degrees of freedom,using quasi-steady aero model,the nonlinear coupledrotor/fuselage equation was founded.The periodic solution of blades and fuselage were obtained through aeroe lastic coupledtrim using temporal finite element method.Peters.dynamic inflow modelwas adopted for vehicle stability.A calculation program was builtup,which offered the blade responses,hubloads and the rotor pitch controls.The correlation between analytical results and related literatures is good.The converged solution simultaneously satisfies the blade and the vehicle equilibrium equations.
- nonlinear /
- aeroelas ticity /
- rotor/fuselage coupling /
- temporal finite element method /
- stability

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参考文献(14)

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