【摘要】：加筋板特有的結(jié)構(gòu)形式能有效減輕結(jié)構(gòu)重量和提高承載能力,被廣泛應(yīng)用于航空航天結(jié)構(gòu)。三維機(jī)織復(fù)合材料加筋板采用連續(xù)纖維整體織造成型,具有傳統(tǒng)層合復(fù)合材料加筋板所沒有的獨(dú)特優(yōu)勢:Z向纖維提高厚度方向剛度和強(qiáng)度,能有效抑制分層和改善連接區(qū)域性能。因此,對其壓縮性能的研究具有重要的實(shí)用價(jià)值和工程意義。本文所研究的加筋板采用兩種不同的機(jī)織結(jié)構(gòu):底板為淺交直聯(lián)結(jié)構(gòu),筋條為正交三向結(jié)構(gòu),兩者通過由筋條內(nèi)引出的Z向纖維穿過底板連成一體。首先,研究三維機(jī)織加筋板預(yù)制件的機(jī)織工藝和內(nèi)部細(xì)觀結(jié)構(gòu),建立了四種不同結(jié)構(gòu)形式的細(xì)觀模型,包括淺交直聯(lián)結(jié)構(gòu)、淺交直聯(lián)+法向紗結(jié)構(gòu)、正交三向結(jié)構(gòu)和“T型”連接結(jié)構(gòu),進(jìn)行有限元分析得到各單胞的彈性性能,并研究了“T型”連接結(jié)構(gòu)的Z向強(qiáng)度性能。然后,用四種單胞的集合重新構(gòu)建加筋板,基于Hashin失效準(zhǔn)則進(jìn)行三維損傷擴(kuò)展模擬,得到了加筋板的壓縮性能。最后,采用樹脂傳遞模塑成型工藝復(fù)合成型三維機(jī)織復(fù)合材料加筋板實(shí)驗(yàn)件,進(jìn)行壓縮實(shí)驗(yàn)研究其破壞機(jī)理。仿真結(jié)果與實(shí)驗(yàn)結(jié)果吻合較好,論證了本文所用研究方法的合理性和有效性。傳統(tǒng)層合復(fù)合材料加筋板的主要失效模式為分層破壞或筋板間脫粘失效,本文所研究的三維機(jī)織復(fù)合材料加筋板,其底板與筋條的連接區(qū)域在壓縮破壞過程中均不會發(fā)生分離,體現(xiàn)了其獨(dú)特優(yōu)勢。底板與筋條的主要失效模式均為經(jīng)向纖維壓縮失效,底板的損傷從加載端兩側(cè)向中央擴(kuò)展,最終導(dǎo)致了整體壓縮破壞。本文的工作在機(jī)械結(jié)構(gòu)力學(xué)及控制國家重點(diǎn)實(shí)驗(yàn)室完成。
[Abstract]:The special structure form of stiffened plate can effectively reduce the weight of the structure and improve the load-carrying capacity, so it is widely used in aerospace structures. The three-dimensional woven composite stiffened plate is woven by continuous fiber, which has the unique advantage of traditional laminated composite stiffened plate: Z-direction fiber increases the stiffness and strength of the thickness direction. It can effectively suppress the delamination and improve the performance of the connection area. Therefore, the study of its compression performance has important practical value and engineering significance. The stiffened plate studied in this paper adopts two different woven structures: the base plate is a shallow intersecting and direct structure, and the bar is an orthogonal three-way structure. The two are connected through the Z-direction fiber drawn from the bar through the floor. Firstly, the weaving process and internal meso-structure of the three-dimensional woven stiffened plate preform are studied, and four kinds of mesoscopic models are established, including the light cross direct structure, the shallow cross direct normal yarn structure, the structure of the three dimensional woven stiffened plate preform, and the internal meso-structure of the three-dimensional woven stiffened plate preform. The elastic properties of each cell are obtained by finite element analysis of the orthogonal three-way structure and the "T-type" connection structure. The Z-direction strength performance of the "T-type" connection structure is studied. Then, the stiffened plate is reconstructed from the set of four kinds of cells. Based on the Hashin failure criterion, the three-dimensional damage expansion simulation is carried out, and the compression performance of the stiffened plate is obtained. Finally, the three-dimensional woven reinforced composite plate was fabricated by resin transfer molding process, and the failure mechanism was studied by compression experiment. The simulation results are in good agreement with the experimental results, and the rationality and effectiveness of the research methods used in this paper are proved. The main failure modes of the traditional laminated composite stiffened plates are delamination failure or debonding failure between the stiffened plates. The three-dimensional woven composite stiffened plates studied in this paper do not separate the connecting regions between the bottom plate and the ribbons in the process of compression failure, and the main failure modes of the laminated composite stiffened plates are delamination failure or debonding failure. It embodies its unique advantages. The main failure modes of the bottom plate and the bar are the longitudinal fiber compression failure, and the damage of the bottom plate extends from both sides of the loading end to the center, which finally leads to the overall compression failure. The work of this paper is completed in the State key Laboratory of Mechanical structure Mechanics and Control.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2017
【分類號】：TB33

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