民用飞机尾翼鸟撞试验有限元仿真及安全性评估

发布时间：2019-05-18 20:25

【摘要】：随着我国国产民用飞机的研制与投入运营,飞机结构作为完全由我国独立自主研制的部分,其适航审定与管理显得愈加重要。其中针对飞机结构的鸟撞问题,由于严重影响飞行安全而且无法避免,因此结构相关的抗鸟撞设计及其适航符合性审定成为了目前适航领域研究的一个重点。由于用于验证抗鸟撞设计的鸟撞试验成本昂贵,因此,可以通过鸟撞有限元仿真与分析,达到优化设计、安全评估和减少试验的目的。本文,针对飞机尾翼前缘结构,开展了有限元仿真建模,以及在此基础上的仿真分析和安全性评估研究,具体包括以下几个方面:首先,研究了鸟体几何模型,结合适航规章中的鸟重要求,研究了明胶鸟弹的形状尺寸。为了描述鸟体在高速冲击过程中所表现出的流体特性,鸟体的材料模型采用了状态方程,而鸟体的有限元模型则通过光滑粒子流体动力学的方法进行了离散化处理。其次,通过冲击仿真建模,主要从损伤尺寸和吸能特性等角度,分析和研究了不同纤维铺层角度及组成形式下的纤维金属层合板复合材料和铝合金材料的抗冲击性能,并根据研究结果对结构材料进行了优化选取。然后,结合所研究成果,从三维数模构建到有限元建模再到仿真分析,完整开展了尾翼前缘结构的鸟撞仿真研究,根据数值仿真结果对不同冲击能量下的结构损伤尤其是结构关键部件的损伤进行了对比分析。最后,以鸟撞适航条款和我国现有符合性审定方法为基础,从定性与定量角度,对尾翼前缘的鸟撞安全性进行了评估,为今后相关领域的研究提供参考。
[Abstract]:With the development and operation of domestic civil aircraft, the airworthiness examination and management of aircraft structure, as a part developed independently by our country, is becoming more and more important. Aiming at the bird collision problem of aircraft structure, because it seriously affects the flight safety and can not be avoided, the structure-related anti-bird collision design and its airworthiness conformity verification has become a focus in the field of airworthiness at present. Because the bird impact test used to verify the anti-bird collision design is expensive, the finite element simulation and analysis of bird collision can be used to optimize the design, evaluate the safety and reduce the test. In this paper, aiming at the leading edge structure of aircraft tail, the finite element simulation modeling is carried out, and the simulation analysis and safety evaluation on this basis are carried out, including the following aspects: firstly, the geometric model of bird body is studied. According to the requirements of bird weight in airworthiness regulations, the shape and size of gelatin bird bomb were studied. In order to describe the fluid characteristics of the bird body in the process of high speed impact, the material model of the bird body adopts the equation of state, while the finite element model of the bird body is discretized by the method of smooth particle hydrodynamics. Secondly, through impact simulation modeling, the impact resistance of fiber metal laminates and aluminum alloy composites with different fiber laying angles and composition forms is analyzed and studied from the point of view of damage size and energy absorption characteristics. According to the research results, the structural materials are optimized and selected. Then, combined with the research results, from the three-dimensional digital model construction to the finite element modeling and then to the simulation analysis, the bird collision simulation research of the tail wing leading edge structure is carried out completely. According to the numerical simulation results, the structural damage, especially the damage of key parts of the structure, under different impact energy is compared and analyzed. Finally, based on the airworthiness clause of bird collision and the existing conformity examination and approval methods in China, the safety of bird collision in the leading edge of tail wing is evaluated qualitatively and quantitatively, which provides a reference for the research in related fields in the future.
【学位授予单位】：南京航空航天大学
【学位级别】：硕士
【学位授予年份】：2017
【分类号】：V216;V328

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