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混合边界子结构的航空发动机机匣模型修正

曹芝腑 姜东 吴邵庆 费庆国

曹芝腑, 姜东, 吴邵庆, 费庆国. 混合边界子结构的航空发动机机匣模型修正[J]. 航空动力学报, 2017, 32(11): 2695-2704. doi: 10.13224/j.cnki.jasp.2017.11.017
引用本文: 曹芝腑, 姜东, 吴邵庆, 费庆国. 混合边界子结构的航空发动机机匣模型修正[J]. 航空动力学报, 2017, 32(11): 2695-2704. doi: 10.13224/j.cnki.jasp.2017.11.017
Model updating of an aeroengine casing based on the mixed boundary substructure[J]. Journal of Aerospace Power, 2017, 32(11): 2695-2704. doi: 10.13224/j.cnki.jasp.2017.11.017
Citation: Model updating of an aeroengine casing based on the mixed boundary substructure[J]. Journal of Aerospace Power, 2017, 32(11): 2695-2704. doi: 10.13224/j.cnki.jasp.2017.11.017

混合边界子结构的航空发动机机匣模型修正

doi: 10.13224/j.cnki.jasp.2017.11.017
基金项目: 教育部新世纪优秀人才支持计划资助项目(NCET-11-0086); 国家自然科学基金(11572086,11402052,11602112)

Model updating of an aeroengine casing based on the mixed boundary substructure

  • 摘要: 提出了一种基于混合边界模态综合的复杂结构有限元模型修正方法。其主要步骤包括:①子结构划分,根据结构形式划分待修正区域,得到子结构和残余结构;②缩聚和装配,利用混合边界模态综合法,将子结构内部自由度集缩聚至混合边界自由度集,得到子结构缩聚矩阵,并与残余结构的系统矩阵进行装配;③修正,基于灵敏度分析方法,对装配后的残余结构进行参数修正。将该方法应用于航空发动机外机匣的精细化有限元建模及模型修正研究,针对局部连接结构参数修正,子结构模型修正方法的参数收敛后最大误差为064%,其计算效率提高了515倍。算例结果表明,该方法在保证修正精确度的同时,能提高大规模复杂结构有限元模型修正的计算效率。

     

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出版历程
  • 收稿日期:  2016-04-06
  • 刊出日期:  2017-11-28

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