直升机尾传动轴弹击损伤仿真与试验验证

Simulation and Experimental Verification of Helicopter Tail Drive Shaft Impact Damage

根据直升机尾传动轴抗弹击设计要求,首先基于LS-DYNA显式动力学分析软件,采用Johnson-Cook本构模型和失效模型建立了尾传动轴弹击损伤预测模型,并结合尾传动轴弹击试验进行验证,结果表明弹击损伤预测结果与弹击试验结果吻合较好。然后,结合建立的弹击损伤预测模型,开展弹击损伤的主要影响因素研究,结果表明影响弹击损伤的主要因素为弹击入射偏移量及入射角度,弹击速度对弹击损伤影响较小。最后,建议后续在进行尾传动轴弹击试验及弹击后承载运转验证试验时,选取切边大角度工况开展,以保证尾传动轴在极限弹击工况下仍能够保证安全运转。

According to the anti-bullet requirements of the helicopter tail shaft,the ballistic damage prediction model was established based on the LS-DYNA explicit dynamic analysis software and the Johnson-cook constitutive and failure model.It’s showed that the predictions results are in good agreement with ballistic test results.Then,combined with the established model,the main influencing factors of projectile damage were studied.The results showed that the main factors were projectile offset and incident angle,and that projectile velocity had little influence on projectile damage.Finally,it is suggested that the ballistic test and the subsequent verification test of the tail shaft should be carried out under the large angle trimming working condition,so as to ensure that the tail drive shaft can still operate safely under the ultimate impact condition。