某直升机前舱罩对全机动力学模型影响研究

英文篇名：Study on the Effects of Front Cabin Shell on a Helicopter Dynamics Model
中文刊名：机电产品开发与创新
英文刊名：Development & Innovation of Machinery & Electrical Products
作者：李湘萍
英文作者：LI Xiang-Ping ; Civil Aviation University of China
中文关键词：直升机 ; 有限元 ; 动力学模型 ; 前舱罩 ; 模态分析
英文关键词：helicopter ; FEA ; dynamics model ; front cabin shell ; modal analysis
出版日期：2013-09-28
机构：中国民航大学;
年：2013
期：05
出版单位：机电产品开发与创新

摘要

以某直升机全机复杂结构为研究对象,采用有限元建立了全机动力学理论模型。该直升机前舱罩壳为有机玻璃特殊工艺成形,建模难度大,为此开展了专项试验研究。基于试验结果利用MPC技术建立了带罩壳的全机动力学计算模型。通过计算,得到前8阶模态频率误差水平为5%左右的高精度模态分析结果。
The structure of one certain helicopter has been studied and the whole dynamics model is established on base of Finite element analysis(FEA). Since the front cabin shell is made of Plexiglas with complicated shape, it's hard to be modeling. Multi-point constraints(MPC)technique of FEA is used to modeling the front cabin shell based on special experiments. By this means, the whole dynamics model with high precision is obtained, and the max error of the first 8 order model frequency of this helicopter is controlled on the level of 5%.

引文

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