摘要
基于金属结构的张力场理论,考虑复合材料的特点,适当地引入假设,提出了一种复合材料翼梁的后屈曲计算方法,并与4mm左右中等厚度腹板的复合材料翼梁试验结果进行对比。结果表明,该方法可以较为准确的预测复合材料翼梁进入张力场后的应力分布和翼梁的破坏载荷,弥补了复合材料翼梁后屈曲计算方法的缺失。
Based on the diagonal tension theory of metal structure, considered the characteristics of the composite structure, induced some hypothesis, presented a post buckling method for composite wing spar, and compared with the test result of medium thickness composite wing spar about 4mm. The results showed that, the stress distribution and the invalidation load for the composite wing spar can be forecast by the method. The method makes up the deifciency of post buckling calculation for the composite wing spar.
出处
《航空科学技术》
2014年第12期21-25,共5页
Aeronautical Science & Technology
关键词
复合材料翼梁
后屈曲
张力场
composite spar
post buckling
diagonal tension
