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  本文選題：復合材料層合板 + 預置分層　； 參考：《哈爾濱工業(yè)大學》2015年碩士論文

【摘要】：由于復合材料具有十分出色的材料性能,并且密度較小,因此在飛行器結構設計被大量使用。然而復合材料的屈曲分層及其分層擴展現(xiàn)象嚴重影響著復合材料結構的穩(wěn)定性,因此對復合材料屈曲行為及其分層擴展的研究有著十分重要的意義。本文針對復合材料層合板設計了一系列的預置分層,包括不同分層位置、分層尺寸、分層大小以及分層數(shù)量等作為變量,設置預置分層,從而研究不同預置分層對層合板屈曲載荷、分層擴展及其疲勞壽命的影響。本文首先用PATRAN對含預置分層層合板進行數(shù)值模擬,得到其屈曲臨界載荷,再取不同的的屈曲載荷的百分比加載,觀察層合板的分層擴展趨勢。然后再對無損傷層合板進行屈曲模擬,得到其屈曲臨界載荷,與含預置分層層合板進行對比,分析其不同分層因素對復合材料層合板屈曲載荷和承載能力的影響。然后分別對無損傷復合材料層合板和含預置分層復合材料層合板進行壓縮實驗,得到其屈曲載荷,進行分析,再與數(shù)值模擬的結果進行對比分析。最后對含預置分層層合板進行疲勞實驗,得到不同預置分層層合板的疲勞壽命次數(shù),然后分析不同預置分層對層合板疲勞壽命的影響。從而得到如下結論:1、當預置分層尺寸、形狀均相同時,預置分層距離層合板中心層越遠,層合板承載能力下降越大,承載能力越弱。2、當預置分層位置、形狀均相同時,預置分層的分層面積越大,層合板的承載能力下降越大,承載能力越弱。3、當預置分層尺寸、位置均相同時,預置分層為圓形的層合板比預置分層為矩形的層合板承載能力弱。4、預置分層的分層數(shù)目越多,層合板的承載能力下降越多,越容易發(fā)生屈曲。5、耦合預制分層中圓心位于試驗件中心的圓形預置分層比預置分層位于邊緣的矩形預置分層承載能力下降更多,更容易發(fā)生屈曲,從而破壞。6、預置分層層合板的擴展趨勢為分層先沿著垂直加載方向進行擴展,然后再沿著平行加載方向進行擴展。7、含預置中央分層層合板的抗疲勞能力較強,對其施加80%屈曲載荷進行疲勞實驗不容易引起它的分層擴展。含預置邊緣分層層合板的抗疲勞能力較弱,對其施加80%屈曲載荷進行疲勞實驗容易引起它的分層擴展。
[Abstract]:Because of its excellent material properties and low density, composite materials are widely used in aircraft structure design. However, the buckling delamination and delamination propagation of composites seriously affect the stability of composite structures, so it is of great significance to study the buckling behavior and delamination propagation of composites. In this paper, a series of preset delamination is designed for composite laminates, including different delamination position, delamination size, delamination size and number of delamination as variables. The effects of different pre-delamination on buckling load, delamination propagation and fatigue life of laminated plates are studied. In this paper, PATRAN is used to simulate the critical buckling load of laminated plates with preset layers, and then different percentages of buckling loads are taken to observe the delamination expansion trend of laminated plates. Then the critical buckling load of the laminated laminates without damage is simulated and compared with the laminated plates with prefabricated laminates. The effects of different delamination factors on the buckling load and load-carrying capacity of composite laminated plates are analyzed. Then the buckling load of the laminated laminates without damage and the laminated laminates with prefabricated laminates are analyzed and compared with the results of numerical simulation. Finally, the fatigue life times of different preset laminated laminates are obtained by fatigue experiments, and the influence of different preset layers on the fatigue life of laminated plates is analyzed. The following conclusion can be drawn as follows: 1. When the size and shape of the preset layer are homogeneous, the further the preset delamination is from the central layer of the laminate, the greater the load capacity of the laminated plate is, and the weaker the load-carrying capacity of the laminated plate is, when the preset delamination position is at the same time, the shape is homogeneous at the same time. The larger the stratification area is, the greater the load capacity of laminates decreases, and the weaker the bearing capacity is. 3. When the size of the preset layering is equal, the position of the laminated laminates is homogeneous at the same time. The load-carrying capacity of laminated plates with circular prelayed layers is weaker than that of rectangular laminated plates. The larger the number of layers, the more the load-carrying capacity of laminated plates decreases. The more prone to buckling. 5, in the coupled prefabricated delamination, the load capacity of the circular preset delamination located at the center of the test piece is much lower than that of the rectangular preset delamination at the edge of the preset delamination, and the buckling is more likely to occur. As a result, the expansion trend of prefabricated laminated laminates is that the delamination extends first along the vertical loading direction and then along the parallel loading direction. The fatigue resistance of the preset central laminated laminates is stronger. The fatigue test of 80% buckling load does not easily lead to its delamination propagation. The fatigue resistance of laminated laminated plates with preset edges is weak, and the fatigue test of the laminated plates with 80% buckling load will lead to its delamination expansion.
【學位授予單位】：哈爾濱工業(yè)大學
【學位級別】：碩士
【學位授予年份】：2015
【分類號】：TB33

【引證文獻】

相關會議論文 前1條

1 盧智先;矯桂瓊;王平安;朱勝利;;含分層損傷的復合材料層合板壓縮力學行為的實驗研究[A];復合材料——基礎、創(chuàng)新、高效：第十四屆全國復合材料學術會議論文集（下）[C];2006年

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本文編號：1843310