| 直升机复合材料桨叶振动失效分析 |
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| 引用本文： | 王军,冯国旭,杨亚东,程小全.直升机复合材料桨叶振动失效分析[J].失效分析与预防,2011,6(2):80-84,118. |
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| 作者姓名： | 王军 冯国旭 杨亚东 程小全 |
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| 作者单位： | 北京航空航天大学,航空科学与工程学院,北京,100191 |
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| 基金项目： | 凡舟科研基金，唯实青年教师基金 |
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| 摘 要： | 针对某直升机复合材料旋翼桨叶,在没有对复杂结构进行简化的情况下,利用ANSYS有限元软件的参数化语言(APDL)建立完整的有限元模型.该模型不仅考虑了大梁、蒙皮和加强梁等主承力结构,还考虑了大梁内抗扭层、前缘包铁和前缘配重等次承力结构.利用该模型,计算桨叶在额定转速下的前5阶固有模态和频率.结果表明:前5阶模态不存在振...
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| 关 键 词： | 直升机 复合材料 桨叶 振动 模态 频率 |
Vibration Failure of Helicopter Composite Blade |
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| WANG Jun,FENG Guo-xu,YANG Ya-dong,CHENG Xiao-quan.Vibration Failure of Helicopter Composite Blade[J].Failure Analysis and Prevention,2011,6(2):80-84,118. |
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| Authors: | WANG Jun FENG Guo-xu YANG Ya-dong CHENG Xiao-quan |
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| Affiliation: | WANG Jun,FENG Guo-xu,YANG Ya-dong,CHENG Xiao-quan(School of Aeronautical Science and Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China) |
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| Abstract: | Regarding a certain helicopter composite rotor blade,finite element method was used to create the integral model through APDL ANSYS without simplifying structure.Research not only about main structures like beam,skin,spar but substructures like inner twist wrap,nose crap,leading edge counter weight was considered in the model.Using this model,the first five natural vibration frequencies and modes of the blade were worked out.The results show that there is no vibrational coupling between the first five modes... |
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| Keywords: | helicopter composite blade vibration mode frequency |
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