民机货舱支柱对机身段抗坠撞性能的影响
Effect of Rigidity of Strut on Crashworthiness of Civil Aircraft

针对某小型民机典型机身段，采用对货舱支柱结构预制缺口的措施实现支柱压缩刚度的改变。运用HyperMesh软件建立3种不同刚度支柱的3框段机身结构有限元模型，应用LS-Dyna有限元软件对模型进行了坠撞仿真，对比分析在垂直坠撞速度为7m/s时，3种机身段的变形模式、吸能模式、速度时间历程曲线和加速度时间历程曲线。结果表明，在坠撞过程中，支柱刚度过大或过小均会对乘员的生存带来严重威胁，对支柱进行合理的缺口预制可有效控制机身段变形模式，改善飞机抗坠撞性能。
Based on the small civil aircraft, three finite element models of fuselage section with different strut rigidity are developed by HyperMesh software. The impact characteristics of fuselage sections subjected to 7m/s vertical velocity are analyzed using the explicit, nonlinear transient-dynamic finite element code, LS-Dyna. A contrastive analysis on failure mode, energy absorption, velocity histories and acceleration histories of different fuselage sections is introduced. The results show that a too high or too low strut stiffness will bring threat to the survival of passengers. An advisable design of strut will impose an effective control on crash failure and reduce the dynamic response, which will finally improve the crashworthiness of aircraft