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基于直升机悬停时桨叶气、弹稳定性优化研究

发表时间:2008-01-31  浏览量:1909  下载量:751
全部作者: 王红州,刘勇,张呈林
作者单位: 南京航空航天大学直升机旋翼动力学国家重点实验室
摘 要: 本文通过对直升机悬停时旋翼挥舞、摆振运动微分方程的分析,判断出旋翼桨叶气弹稳定性运动条件。提出了在多约束条件下的敏度分析方法,使用不同优化方法对模型参数进行优化研究。结果表明,在气弹稳定性、自转惯量和振动固有频率等多约束条件下,实现自转惯量提高到原来的1.12倍,桨叶重量减少4.4%~12.3%,优化性能良好。
关 键 词: 直升机工程;桨叶气弹稳定性;设计参数;敏度分析;自转惯量
Title: The helicopter blades aeroelastic stability optimization in hover
Author: WANG Hongzhou, LIU Yong, ZHANG Chenglin
Organization: National Key Laboratory of Rotorcraft Aeromechanics, Nanjing University of Aeronautics and Astronautics
Abstract: This chapter analyzes the different equations for the rotor flap and lag motion in hover. From which it can judge aeroelastic stability. This paper provided the sensitivity analysis method under the condition of multiple constraints. It realizes the optimization of the blade designing parameter model with different optimal methods. At last, compared the result of optimization to the model designed before, it identified that the optimum solution results in a 4.4%~12.3% reduction of the total mass of the rotor blade as well as a increasing in the peak-to-peak blade autoratorational inertia of 1.12 times, with which constraints were imposed on blade rotating frequencies, autorotational inertia, aeroelastic stability and so on.
Key words: helicopter engineering; blade areoelastic stability; designing parameters; sensitivity analysis; autoratorational inertia
发表期数: 2008年5月第2期
引用格式: 王红州,刘勇,张呈林. 基于直升机悬停时桨叶气、弹稳定性优化研究[J]. 中国科技论文在线精品论文,2008,1(2):158-162.
 
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