| 2024-T3铝合金动力学实验及其平板鸟撞动态响应分析 |
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| 引用本文： | 刘富,张嘉振,童明波,胡忠民,郭亚洲,臧曙光.2024-T3铝合金动力学实验及其平板鸟撞动态响应分析[J].振动与冲击,2014,33(4):113-118. |
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| 作者姓名： | 刘富 张嘉振 童明波 胡忠民 郭亚洲 臧曙光 |
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| 作者单位： | 1. 中国商飞北京民用飞机技术研究中心，北京 102211；2. 南京航空航天大学 飞行器先进设计技术国防重点学科实验室，南京 210016；3. 西北工业大学 航空学院，西安 710012；4. 中国建筑材料检验认证中心，北京 100024 |
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| 基金项目： | 中国博士后科学基金资助项目(20110490765) |
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| 摘 要： | 通过电子万能试验机和分离式霍普金森拉杆(SHTB)拉伸试验分别获得2024-T3铝合金材料准静态和高应变率两种应变率下的应力-应变曲线。铝合金材料的本构关系由能够反映材料硬化效应和应变率强化效应的Johnson-Cook材料模型描述,方程中的4个参数通过不同应变率下的应力-应变曲线拟合得到。基于瞬态动力学软件PAM-CRASH,结合材料动态力学性能试验所获得的2024-T3铝合金Johnson-Cook模型方程,耦合光滑粒子流体动力学(SPH)方法和有限元(FE)方法建立2024-T3铝合金平板的鸟撞数值模型,数值计算所得动态响应与鸟撞试验结果吻合较好,表明建立的鸟撞数值计算模型是合理、可靠的,整个分析流程从材料动态力学性能试验、鸟撞数值计算到最终的鸟撞试验验证为飞机结构的抗鸟撞设计与分析提供了有力的参考。
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| 关 键 词： | 动态响应 数值计算 本构模型 鸟撞 试验 |
| 收稿时间： | 2012-12-17 |
| 修稿时间： | 2013-3-11 |
Dynamic mechanical experiment and bird impact dynamic response analysis of 2024-T3 aluminum alloy plate |
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| Liu Fu,Zhang Jia-zhen,Tong Ming-bo,Hu Zhong-min,Guo Ya-zhou,Zang Shu-guang.Dynamic mechanical experiment and bird impact dynamic response analysis of 2024-T3 aluminum alloy plate[J].Journal of Vibration and Shock,2014,33(4):113-118. |
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| Authors: | Liu Fu Zhang Jia-zhen Tong Ming-bo Hu Zhong-min Guo Ya-zhou Zang Shu-guang |
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| Affiliation: | 1. Aeronautical Science & Technology Research Institute of COMAC, Beijing 102211, China;2. Key Laboratory of Fundamental Science for National Defense-Advanced Design Technology of Flight Vehicle, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;3. College of Aeronautics, Northwestern Polytechnical University, Xi’an 710012, China;4. China Building Material Test & Certification Center, Beijing 100024, China |
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| Abstract: | Stress-strain curves at quasi-static and high strain rate of 2024-T3 aluminum alloy are measured using dynamic tensile tests by the electronic universal testing machine and split Hopkinson tensile bar (SHTB). Constitutive model of aluminum alloy is described by Johnson-Cook model which can reflect strain and strain rate hardening effect. 4 parameters in Johnson-Cook equation are fitted by the stress-strain curves at different strain rates. By coupling Smooth Particle Hydrodynamics (SPH) method and Finite Element (FE) method, combining with the Johnson-Cook equation of 2024-T3 aluminum alloy, the numerical model of bird impact on a 2024-T3 aluminum alloy square plate is established using the transient dynamic software PAM-CRASH. Dynamic responses of the plate by numerical calculation agree well with the experimental results, which shows that the numerical calculation is reasonable and reliable. The analysis process including material dynamic mechanical test, numerical calculation and bird impact experimental verification provides reference for anti-bird impact design and analysis of aircraft structure. |
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| Keywords: | dynamic responsenumerical calculationconstitutive modelbird impactexperiment |
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