【摘要】：隨著我國(guó)國(guó)產(chǎn)民用飛機(jī)的研制與投入運(yùn)營(yíng),飛機(jī)結(jié)構(gòu)作為完全由我國(guó)獨(dú)立自主研制的部分,其適航審定與管理顯得愈加重要。其中針對(duì)飛機(jī)結(jié)構(gòu)的鳥(niǎo)撞問(wèn)題,由于嚴(yán)重影響飛行安全而且無(wú)法避免,因此結(jié)構(gòu)相關(guān)的抗鳥(niǎo)撞設(shè)計(jì)及其適航符合性審定成為了目前適航領(lǐng)域研究的一個(gè)重點(diǎn)。由于用于驗(yàn)證抗鳥(niǎo)撞設(shè)計(jì)的鳥(niǎo)撞試驗(yàn)成本昂貴,因此,可以通過(guò)鳥(niǎo)撞有限元仿真與分析,達(dá)到優(yōu)化設(shè)計(jì)、安全評(píng)估和減少試驗(yàn)的目的。本文,針對(duì)飛機(jī)尾翼前緣結(jié)構(gòu),開(kāi)展了有限元仿真建模,以及在此基礎(chǔ)上的仿真分析和安全性評(píng)估研究,具體包括以下幾個(gè)方面:首先,研究了鳥(niǎo)體幾何模型,結(jié)合適航規(guī)章中的鳥(niǎo)重要求,研究了明膠鳥(niǎo)彈的形狀尺寸。為了描述鳥(niǎo)體在高速?zèng)_擊過(guò)程中所表現(xiàn)出的流體特性,鳥(niǎo)體的材料模型采用了狀態(tài)方程,而鳥(niǎo)體的有限元模型則通過(guò)光滑粒子流體動(dòng)力學(xué)的方法進(jìn)行了離散化處理。其次,通過(guò)沖擊仿真建模,主要從損傷尺寸和吸能特性等角度,分析和研究了不同纖維鋪層角度及組成形式下的纖維金屬層合板復(fù)合材料和鋁合金材料的抗沖擊性能,并根據(jù)研究結(jié)果對(duì)結(jié)構(gòu)材料進(jìn)行了優(yōu)化選取。然后,結(jié)合所研究成果,從三維數(shù)模構(gòu)建到有限元建模再到仿真分析,完整開(kāi)展了尾翼前緣結(jié)構(gòu)的鳥(niǎo)撞仿真研究,根據(jù)數(shù)值仿真結(jié)果對(duì)不同沖擊能量下的結(jié)構(gòu)損傷尤其是結(jié)構(gòu)關(guān)鍵部件的損傷進(jìn)行了對(duì)比分析。最后,以鳥(niǎo)撞適航條款和我國(guó)現(xiàn)有符合性審定方法為基礎(chǔ),從定性與定量角度,對(duì)尾翼前緣的鳥(niǎo)撞安全性進(jìn)行了評(píng)估,為今后相關(guān)領(lǐng)域的研究提供參考。
[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.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：V216;V328

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