飞机典型结构抗鸟撞设计与分析
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摘要
飞机在起飞和着陆过程中以及在低空、高速飞机过程中,都可能和飞鸟发生碰撞,鸟撞问题日益成为危及飞行安全的隐患,飞行器结构鸟撞问题越来越引起人们的注意。飞机典型结构(如挡风玻璃、雷达罩、翼面前缘等)的抗鸟撞研究是各国在飞机设计环节中需要注意的问题。对于结构抗鸟撞的设计最初通过实验来进行研究,鸟撞试验也是最终、最有效的检验方法。常规的、全尺寸试验方法存在费时、费力、成本高昂的缺陷。而且现有的鸟撞试验数据分散严重,因而对结构设计的指导作用较低。随着计算机技术和有限元理论的发展,为了避免大量的鸟撞实验引起过高的成本,通过引入有限元数值模拟办法对鸟撞问题进行研究,最终通过试验验证的办法解决抗鸟撞设计是十分有效的方法。
本文首先分析了飞机鸟撞事故对飞机结构不同部位的破坏,在对鸟撞问题的特点和国内外所运用研究方法进行总结的基础上开展了全面系统的研究。结合作者多年来对军用飞机结构设计的经验,首先针对军用飞机特别是军用作战飞机的任务剖面特点,对其复合材料结构和金属结构的抗鸟撞设计目标进行了探讨,提出了比较明确的设计指标,对当前已有军、民用鸟撞规范进行了有益的补充。在鸟撞试验方面,详细介绍了国内鸟撞试验方法、实验测量装置,结合作者所在成飞公司近年来对某型飞机风挡开展的大量鸟撞试验,讨论和总结了鸟撞破坏过程、破坏位置、影响因素等。在此基础上,利用大变形、粘弹性、接触—碰撞等有限元分析的基本理论、首次在国内的飞机结构鸟撞仿真计算中,引入了光滑粒子法(SPH)与有限元耦合的算法。通过与试验结果的对比,对该算法在鸟撞仿真中的应用进行了成功的验证。本文系统阐述了该算法的基础理论,并利用SPH算法对飞机典型结构雷达罩、机尾翼前缘模型进行了鸟撞仿真研究,得到了很有意义的结论。最后在对飞机典型结构风挡、雷达罩、机尾翼前缘的试验与仿真研究的基础上,对飞机典型结构的抗鸟撞设计准则进行了探讨。本文的研究成果对于今后新机研制中,结构抗鸟撞设计与分析工作有一定的参考价值。
With the development of high-speed performance at low altitude aircraft and highly effective work on protecting eco-environment engineering, the problem of bird strike has been becoming a hidden trouble which increasingly endangers the flight safe. The problem of aircraft structure bird strike has been brought to people’s notice more and more. Great attention to anti-bird impact design of aircraft typical structures is paid by aircraft designers in all countries. Anti-bird impact research starts from test that is final and most effective verification method. But the full dimensional test is time-consuming, laborious and high cost. Due to the dispersal result of bird strike test, it is difficult to guide the structure design. Along with development of computer techniques and finite element theories, method which conjoins finite element numerical simulation and bird strike test has been growing up in engineering practice, which is applied to the anti-bird impact design.
The airplane bird strike accidents are summed up and the characteristics and research methods of bird strike problem are summarized in this paper. According to the author’s experience of military aircraft structure design for many years, aiming at mission section characteristic of the avion especially fighters, the target of composite structure and metal structure resist bird strike design was firstly discussed. The relatively specific design target was put forward, which beneficially complements the existing millitary and civil bird strike criterion. According to Chengdu Aircraft Industry Company’s research on bird strike tests, the bird strike test methods, equipments and the windshield bird strike test of an aircraft were introduced particularly. Moreover test results were discussed and summarized. Based on bird strike test, making use of the basic theory of large deformation, viscoelasticity and contact-impact finite element analysis, arithmetic coupling Smoothed Particle Hydrodynamics(SPH) with finite element was inducted in the way of aircraft structure simulation calculating for the first time in our country. Comparing to test results, this arithmetic was successfully validated in the bird strike numerical simulation. Related basic theory of the algorithm is elaborated. The bird strike simulation research on aircraft typical structures such as radome and leading edge of wing and empennage are conducted too and meaningful conclusions was obtained. Based on test and simulation of aircraft windshield, the anti-bird impact design guide line of aircraft typical structures for radome and leading edge of wing and empennage is discussed. Research conclusions of this article have reference value for new aircraft development.
本文首先分析了飞机鸟撞事故对飞机结构不同部位的破坏,在对鸟撞问题的特点和国内外所运用研究方法进行总结的基础上开展了全面系统的研究。结合作者多年来对军用飞机结构设计的经验,首先针对军用飞机特别是军用作战飞机的任务剖面特点,对其复合材料结构和金属结构的抗鸟撞设计目标进行了探讨,提出了比较明确的设计指标,对当前已有军、民用鸟撞规范进行了有益的补充。在鸟撞试验方面,详细介绍了国内鸟撞试验方法、实验测量装置,结合作者所在成飞公司近年来对某型飞机风挡开展的大量鸟撞试验,讨论和总结了鸟撞破坏过程、破坏位置、影响因素等。在此基础上,利用大变形、粘弹性、接触—碰撞等有限元分析的基本理论、首次在国内的飞机结构鸟撞仿真计算中,引入了光滑粒子法(SPH)与有限元耦合的算法。通过与试验结果的对比,对该算法在鸟撞仿真中的应用进行了成功的验证。本文系统阐述了该算法的基础理论,并利用SPH算法对飞机典型结构雷达罩、机尾翼前缘模型进行了鸟撞仿真研究,得到了很有意义的结论。最后在对飞机典型结构风挡、雷达罩、机尾翼前缘的试验与仿真研究的基础上,对飞机典型结构的抗鸟撞设计准则进行了探讨。本文的研究成果对于今后新机研制中,结构抗鸟撞设计与分析工作有一定的参考价值。
With the development of high-speed performance at low altitude aircraft and highly effective work on protecting eco-environment engineering, the problem of bird strike has been becoming a hidden trouble which increasingly endangers the flight safe. The problem of aircraft structure bird strike has been brought to people’s notice more and more. Great attention to anti-bird impact design of aircraft typical structures is paid by aircraft designers in all countries. Anti-bird impact research starts from test that is final and most effective verification method. But the full dimensional test is time-consuming, laborious and high cost. Due to the dispersal result of bird strike test, it is difficult to guide the structure design. Along with development of computer techniques and finite element theories, method which conjoins finite element numerical simulation and bird strike test has been growing up in engineering practice, which is applied to the anti-bird impact design.
The airplane bird strike accidents are summed up and the characteristics and research methods of bird strike problem are summarized in this paper. According to the author’s experience of military aircraft structure design for many years, aiming at mission section characteristic of the avion especially fighters, the target of composite structure and metal structure resist bird strike design was firstly discussed. The relatively specific design target was put forward, which beneficially complements the existing millitary and civil bird strike criterion. According to Chengdu Aircraft Industry Company’s research on bird strike tests, the bird strike test methods, equipments and the windshield bird strike test of an aircraft were introduced particularly. Moreover test results were discussed and summarized. Based on bird strike test, making use of the basic theory of large deformation, viscoelasticity and contact-impact finite element analysis, arithmetic coupling Smoothed Particle Hydrodynamics(SPH) with finite element was inducted in the way of aircraft structure simulation calculating for the first time in our country. Comparing to test results, this arithmetic was successfully validated in the bird strike numerical simulation. Related basic theory of the algorithm is elaborated. The bird strike simulation research on aircraft typical structures such as radome and leading edge of wing and empennage are conducted too and meaningful conclusions was obtained. Based on test and simulation of aircraft windshield, the anti-bird impact design guide line of aircraft typical structures for radome and leading edge of wing and empennage is discussed. Research conclusions of this article have reference value for new aircraft development.
引文
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