| 直升机气动弹性力学发展现状(续) |
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| 引用本文： | 符长青.直升机气动弹性力学发展现状(续)[J].力学进展,1987,17(1):0-0. |
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| 作者姓名： | 符长青 |
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| 作者单位： | 南京航空学院 |
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| 摘 要： | Ⅲ.单片桨叶气动弹性问题的求解1.桨叶离散化方法求解旋翼桨叶气动弹性力学问题的第一步是将连续桨叶离散化,即把一个具有无限多个自由度的连续参数系统离散化为具有有限个自由度的离散系统。常用方法有三种: 1)整体模态方法在直升机旋翼气动弹性力学中,以往用得多的离散方法是整体模态法,或称为整体伽辽金方法。此方法的实质是利用桨叶自由振动振型是线性独立
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| 收稿时间： | 2008-04-22 |
THE DEVELOPMENT AND STATE-OF-THE-ART OF HELICOPTER AERO-ELASTICITY |
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| Fu Chang-qing.THE DEVELOPMENT AND STATE-OF-THE-ART OF HELICOPTER AERO-ELASTICITY[J].Advances in Mechanics,1987,17(1):0-0. |
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| Authors: | Fu Chang-qing |
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| Institution: | Nanjing Aeronautical Institute |
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| Abstract: | This paper gives a comprehensive review of the development of helicopter aeroelasticity in the last fifteen years. The structural, inertia and aerodynamics operators are discussed. The important role of geometric nonline-arities, due to moderate deflections, and aerodynamic stall in the aeroelastic stability and response problems are expounded. Aeroelastic problems for complete rotor are described as well as for coupled rotor/fuselage. |
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| Keywords: | helicopter aeroelasticity coupled rotor/fuselage acroelastic problems |
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