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通过仿真与试验的对比分析,分析结构单元尺寸对飞机尾翼复合材料蒙皮鸟撞模拟精度的影响。基于PAM-CRASH软件,用光滑粒子流体动力学方法建立适航条例所规定鸟体结构模型,用二维壳单元模拟层压板结构,通过试算计算出多种单元尺寸下结构破损的临界速度。结果表明,在层压板不发生破损的情况下,单元尺寸对位移计算结果影响很小;临界破损速度的计算值随着单元尺寸的增大而增大;当层压板单元尺寸为5 mm时,临界破损速度和应变响应与实测结果吻合最好。
Through the comparison and analysis of simulation and experiment, the influence of structural unit size on simulation accuracy of bird-tail collision of aircraft tail composite skin was analyzed. Based on the PAM-CRASH software, a smooth particle hydrodynamics method was used to establish the bird structure model regulated by the airworthiness regulation. The two-dimensional shell element was used to simulate the structure of the laminate, and the critical velocity of structural damage under various unit sizes was calculated through trial calculation. The results show that the unit size has little influence on the displacement calculation results when the laminate is not damaged. The calculated critical breaking speed increases with the unit size. When the unit size of the laminate is 5 mm, The critical damage velocity and strain response agree well with the measured results.