A finite element model including full - scale circular arc windshield glass and the relative parts of the plane is established using ls - dyna3d v . 950 code in the computer simulation and is validated using the result from the test 数值模拟中，建立了包括飞机相关部件的全尺寸有限元模型。鸟体采用ale描述。有限元模型采用ls - dyna进行了分析。
It is a very important project for birds to strike aircraft structures in airframe designs and appiication practices , meanwhiie , which aiso possesses of the values of in - deep scientiflc research and theoretical exploration 鸟体对结构的撞击不仅是飞机结构设计工程及应用实践中的重要课题，同时也具有深入的科学研究价值和理论探讨意义。
Compared the response results with three kinds bird model , the bird gecemetry model and bird material parameter are decided which exactly reflect the liquid characteristic of bird model and the transient response of blade 确定合理的鸟体模型参数,更真实地反映了高速撞击下鸟体的流变特性和叶片的动态响应,对叶片抗鸟撞击能力的评定具有一定的参考价值。
The experiment of the transient response of the blade due to bird impact is completed , and the high speed phorographs are analyzed , then the curves about the displacement of blade tip are drew which are helpful for the caculation of bird material parameter 本文开展了平板叶片鸟撞击瞬态响应的试验,对试验中高速摄影照片进行处理和分析并得出试验中叶尖位移的时间历程,为本文的鸟撞击叶片响应中鸟体材料的进一步计算研究提供了依据。
This research work on bird striking has a long history and already got plentiful achievemellts in theories and experiments , howevef , still a long way no doubt waits to go for sophisticated research work on it more detailed to apply to airframe engineering quantitatively in combination wth the technical reformation of the birdstrike experimelltal system in our laboratory , this thesis deeply studies and analyses the numerica1 computation and simulation methods to birdstrike dynamic response problem based on finite - elemefit - method ( fem ) numerical emulation and modem large - scale scientfic computation software 本文结合我公司鸟撞实验体系技术改造项目，应用有限元数值计算仿真技术及现代大型科学计算工具，对鸟体撞击飞机风挡结构的动力学响应问题进行了系统学习与研究探讨，初步掌握了科学计算方法，获得了计算仿真的实践经验，为今后深入应用大型科学计算手段进行撞击类科学问题的研究以及深入应用于工程实践奠定了强有力的工作基础。
In summary the major research work in this thesis can be drawn as follows : 1 . the techncal data and research information from woridwide aviation history about bird striking to airframe have been collected and reviewed more carefully the evolutions of bird striking load models and fem numerical compatation methods to bird strike also have been sununarized . this informational research makes great help to position further thesis work scientifically 2 本文研究工作可归纳总结为以下三个方面： 1 、较全面整理综述了鸟体撞击飞机结构在国内外航空史上的技术资料以及鸟撞问题理论与工程研究的历史沿革，总结了撞击载荷研究模型、有限元数值计算方法的发展历程等，明确了本文研究工作的科学定位。
3 . wth application of large - scale computational software anasys - dyna , the case of elastic impact to each other of two recta - ngular cross - section rods has been implemented and also compared with theoretical results , which maks good agreement and draws very helpful practical experiences to use some techncal parameters in the program . eventually , the a real - world aircraft windshield shell structure impacted by a flying bird has been simulated through fem numerical computation , and meanime , an engineering predical experimeni of bird sttiking to the windshield in some type of aircraft has been performed 3 、应用大型科学计算程序anasys - dyna ，对弹性体碰撞进行了数值计算验证并与理论结果对比，获得了计算参数应用的实践经验；在此基础上，进行了鸟体撞击飞机风挡结构动力学响应的实际数值计算，与此同时安排了工程鸟体撞击试验，并就两者计算结果给予了细致分析对比，获得了良好的一致性结论。
The scielltific computational theories and methods on bird strike to the windshield of aircraft have been systematically studied and summed up in this thesis , such as fem comptltational principles and procedures to elastic dynamic problems under the conditions of small and non - linear finite deformation , 3d viscous elastic constitutive theory and incremelltal expression under the consideration of the rate effect of non - metallic materials like the aircraft windshield , and the numerical compatational principles and key constitutions for impact - contact dynamic subjects 2 、系统学习并归纳总结了鸟体撞击风挡结构问题中的科学计算理论与计算方法。按照鸟撞问题数值计算方法逐步深入的思路，系统总结了小变形结构动力学有限元数值计算方法、有限变形的几何非线性有限元数值计算方法、粘弹性体非线性形变的本构物理关系；对于实施复杂结构有限元动力学计算的载荷增量方法提出了对newmark差分的改进以及进行材料与几何非线性数值计算的细致步骤。
