發(fā)布時(shí)間：2018-02-10 13:17

  本文關(guān)鍵詞： 復(fù)合材料層合板 鳥撞擊 流固耦合 動(dòng)響應(yīng) 損傷 數(shù)值模擬　出處：《鄭州大學(xué)》2015年碩士論文　論文類型：學(xué)位論文

【摘要】：隨著復(fù)合材料在航空航天上的應(yīng)用越來(lái)越廣,復(fù)合材料層合板的鳥撞問(wèn)題也越來(lái)越受到重視。解決好這一問(wèn)題對(duì)于避免因鳥撞而造成的重大事故或損失有重要意義。當(dāng)前國(guó)內(nèi)外眾多的專家學(xué)者都對(duì)這一問(wèn)題分別從理論分析、實(shí)驗(yàn)探究、數(shù)值模擬以及設(shè)計(jì)規(guī)范四個(gè)方面進(jìn)行了部分研究。本文總結(jié)了鳥撞問(wèn)題的歷史以及國(guó)內(nèi)外對(duì)復(fù)合材料鳥撞問(wèn)題的研究現(xiàn)狀;對(duì)復(fù)合材料層合板鳥撞問(wèn)題相關(guān)的理論進(jìn)行了探究,包括層合板強(qiáng)度理論、鳥撞動(dòng)力學(xué)理論以及ANSYS/LS-DYNA在解決該問(wèn)題中的應(yīng)用;對(duì)鳥撞問(wèn)題中的撞擊載荷鳥體進(jìn)行了詳細(xì)探討,主要包括載荷模擬方式、耦合算法和耦合方式、鳥體本構(gòu)模型、鳥體材料參數(shù)以及鳥體形狀等方面,并對(duì)建立的鳥體模型進(jìn)行了驗(yàn)證,證明了所建模型的合理性;通過(guò)ANSYS/LS-DYNA構(gòu)建了復(fù)合材料層合板鳥撞流固耦合模型,對(duì)其鳥撞動(dòng)響應(yīng)及損傷情況進(jìn)行了詳細(xì)探討,主要包括鳥體與板的撞擊過(guò)程及變形、層合板上接觸壓力的變化、鳥撞過(guò)程的能量變化以及層合板不同損傷形式的擴(kuò)展等內(nèi)容;最后結(jié)合鳥撞過(guò)程中鳥體能量變化以及層合板接觸壓力極值,對(duì)影響層合板抗鳥撞能力的因素進(jìn)行了分析,主要包括層合板材料、鋪層方式、鳥體材料以及鳥體速度四方面的內(nèi)容。通過(guò)本文研究,可以為復(fù)合材料層合板的抗鳥撞設(shè)計(jì)及鳥撞試驗(yàn)提供理論支持。
[Abstract]:As composite materials become more and more widely used in aerospace, The problem of bird collision in composite laminates has been paid more and more attention. It is important to solve this problem for avoiding the serious accidents or losses caused by bird collision. At present, many experts and scholars at home and abroad are interested in this problem. From the theoretical analysis, This paper summarizes the history of bird collision problem and the research status of composite material bird collision problem at home and abroad. The related theories of bird impact problem of composite laminated plate are discussed, including the theory of laminated plate strength, the theory of bird collision dynamics and the application of ANSYS/LS-DYNA in solving this problem, and the impact load of bird body in bird collision problem is discussed in detail. It mainly includes load simulation mode, coupling algorithm and coupling mode, bird body constitutive model, bird body material parameters and bird body shape, etc. The established bird body model is verified, and the rationality of the model is proved. The bird collision fluid-solid coupling model of composite laminated plate was constructed by ANSYS/LS-DYNA. The bird impact response and damage were discussed in detail, including the impact process and deformation of bird body and plate, and the change of contact pressure on laminated plate. The energy change of bird collision process and the expansion of different damage forms of the laminated plate are discussed. Finally, the factors influencing the bird collision resistance of the laminated plate are analyzed by combining the bird body energy change and the contact pressure extremum of the laminated plate during the bird collision process. It mainly includes four aspects: laminate material, layering method, bird body material and bird body velocity. Through the research in this paper, it can provide theoretical support for bird impact design and bird impact test of composite laminates.
【學(xué)位授予單位】：鄭州大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2015
【分類號(hào)】：TB33

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本文編號(hào)：1500603