航空学报 > 2008, Vol. 29 Issue (5): 1150-1156

加筋复合材料结构的冲击载荷识别

严刚,周丽   

  1. 南京航空航天大学 航空宇航学院
  • 收稿日期:2007-07-30 修回日期:2007-12-06 出版日期:2008-09-25 发布日期:2008-09-25
  • 通讯作者: 周丽

Impact Load Identification for Stiffened Composite Structure

Yan Gang,Zhou Li   

  1. College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics
  • Received:2007-07-30 Revised:2007-12-06 Online:2008-09-25 Published:2008-09-25
  • Contact: Zhou Li

摘要: 提出了一种冲击载荷识别方法,同时识别冲击位置并重建冲击载荷时间历程。该方法采用一组适当的参数来表示冲击载荷,将时域内的载荷识别问题转换为参数识别问题;通过最小化冲击响应模型计算结果与实际量测信息之间的差别,智能优化方法自适应地识别出描述冲击位置和载荷时间历程的参数。该方法算法明确、过程简单、通用性强。将此方法应用于复合材料加筋结构的冲击载荷识别,加筋结构等效为材料性质不均匀分布的层板结构,采用假设模态法建立正向冲击响应模型。数值仿真结果表明了本方法的有效性和可应用性。

关键词: 冲击载荷识别, 参数识别, 智能优化方法, 加筋复合材料结构, 假设模态法

Abstract: This article proposes an approach for impact load identification that can identify the impact location and reconstruct the load time history simultaneously. In this study,the impact load is represented by a set of suitable parameters, thus the load identification problem in time domain is transformed to a parameter identification problem. Combining with a forward impact response model, the intelligent optimization algorithm adaptively identifies the impact location and time history by minimizing the difference between the computed analytical results and the measured information. This clear, simple and general method is applied to an impact identification problem for stiffened composite panel. The stiffened composite panel is modeled as an equivalent laminate with varying properties and the forward impact response is obtained using an assumed mode approach. Numerical simulation studies have demonstrated the effectiveness and applicability of the proposed approach.

Key words: impact load identification, parameter identification, intelligent optimization algorithm, stiffened composite structure, assumed mode method

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