摘要
针对结构参数对高平尾布局尾翼振动横态局部化影响进行了研究。考虑到失调本身的不可预知性,在实际结构的基础上设计了质量正失调、质量负失调、刚度正失调、刚度负失调四种可能出现的失调尾翼模型。当失调量为±0.5时,通过模态分析法得到了翼梁和翼肋厚度不同的情况下结构的振动模态局部化度,并讨论了结构自身参数对不同失调原因引起的模态局部化的影响。结果表明:垂尾梁厚度的增加会提高振动模态局部化程度,而平尾梁厚度的影响与之相反,翼肋参数对模态局部化基本无影响;与前梁厚度相比,后梁厚度对结构振动模态局部化的影响较大;当垂尾后梁厚度增加到2.0mm时,0.5kε=-的失调模型的局部化度从0.342变为0.971,这种显著变化在结构设计中需引起注意;此外,结构参数对质量正失调和刚度负失调产生的模态局部化的影响强于质量负失调和刚度正失调。
For mistuned high horizontal tail(HHT), mode localization can significantly change its natural vibration characteristics and then influence its flutter performance. Considering that mistuning in structure is unpredictable, four possible mistuned HHT models are designed, which include increasing mass mistuning(IMM),decreasing mass mistuning(DMM), increasing stiffness mistuning(ISM) and decreasing stiffness mistuning(DSM),respectively. With the mistuning value of ±0.5, the degree of mode localization under different parameters of wing beams and ribs is calculated through modal analysis, and then the effect of structural parameters on mode localization from different reasons are discussed. Numerical results indicate that the degree of mode localization increases with the increase of thicknesses of fin beams and decreases with the increase of thicknesses of horizontal tail beams, while it remains almost the same when changing the parameters of ribs. The effect of parameters of rear beams on mode localization is more significant than that of parameters of front beams. When the thickness of fin rear spar reaches 2.0mm, the degree of mode localization change from 0.342 to 0.971, which is so significant that needs to be concerned. Besides, mode localization resulted from IMM and DSM is more sensitive to the variation of structural parameters than that resulted from DMM and ISM.
出处
《应用力学学报》
CAS
CSCD
北大核心
2014年第1期14-19,2,共6页
Chinese Journal of Applied Mechanics
基金
国家自然基金(51210008)
高等学校学科创新引智计划项目(B07050)
西北工业大学基础研究基金(JCY20130126)
关键词
模态局部化
失调
模态分析
高平尾
结构参数
mode localization
mistuning
mode analysis
high horizontal tail
structural parameter.
