【摘要】：與傳統(tǒng)的直纖維層合結(jié)構(gòu)不同,絲束變角度層合結(jié)構(gòu)是一種鋪層纖維角度連續(xù)變化的變剛度復(fù)合材料,通過鋪絲頭牽引著絲束帶沿特定的軌跡運(yùn)動(dòng),實(shí)現(xiàn)纖維的曲線鋪放,使得纖維角度在同一鋪層上連續(xù)變化,從而擴(kuò)大了復(fù)合材料的設(shè)計(jì)靈活性,充分地利用纖維的方向特性,更好的改善結(jié)構(gòu)性能和減輕結(jié)構(gòu)重量。本文簡述了變剛度復(fù)合材料層合結(jié)構(gòu)的發(fā)展過程及國內(nèi)外研究現(xiàn)狀,以變剛度復(fù)合材料層合板殼為研究對(duì)象,在已有研究的基礎(chǔ)上,通過設(shè)計(jì)絲束鋪放軌跡,對(duì)其力學(xué)性能進(jìn)行研究,主要工作如下:簡述平移法和平行法這兩種纖維鋪放方式,分析容易出現(xiàn)間隙或者重疊區(qū)域的原因,綜合比較兩種方法優(yōu)缺點(diǎn)選擇平移法。介紹層合板(殼)的基本理論和序列響應(yīng)面建模方法,選擇二次函數(shù)造出響應(yīng)面,再通過遺傳算法優(yōu)化獲得原問題的優(yōu)化解。設(shè)計(jì)變剛度層合板纖維曲線軌跡,通過連續(xù)曲線纖維離散化的思想建立了變剛度層合板的有限元模型,分析層合板在單向軸壓和雙向軸壓載荷下纖維軌跡參數(shù)和幾何參數(shù)對(duì)屈曲的影響。討論纖維曲線軌跡和幾何參數(shù)對(duì)層合板頻率的影響,結(jié)合序列響應(yīng)面法,對(duì)變剛度層合板的屈曲和頻率特性進(jìn)行優(yōu)化,獲得的T0、T1優(yōu)化解。給出變剛度(橢)圓柱殼的纖維鋪放路徑和鋪層順序方案,在ANSYS中建立它們的有限元模型;在軸壓,彎矩,扭矩載荷條件下,同時(shí)分析(橢)圓柱殼幾何尺寸對(duì)屈曲性能的影響。然后以臨界屈曲系數(shù)為目標(biāo),優(yōu)化層合殼的屈曲特性。結(jié)果表明:在彎矩載荷作用下,用曲線纖維鋪層θ代替[45/0/-45/90/-45/0/45/90]s層合殼中含有45°直線鋪層,可顯著提高圓柱殼的屈曲性能;通過控制絲束角度連續(xù)變化,改變橢圓柱殼圓周方向的剛度,達(dá)到適當(dāng)?shù)脑黾悠教共糠值膭偠?曲率半徑小的那部分剛度適當(dāng)減小,可以有效的提高橢圓柱殼的屈曲性能。
[Abstract]:Different from the traditional straight fiber laminated structure, the filament bundle variable angle laminated structure is a kind of variable stiffness composite material with continuous change of the fiber laying angle. The angle of the fiber changes continuously on the same layer, which expands the design flexibility of the composite, makes full use of the directional characteristics of the fiber, improves the structure performance and reduces the weight of the structure. In this paper, the development process of the composite laminated structure with variable stiffness and the research status at home and abroad are briefly described. Taking the laminated plate and shell of the variable stiffness composite material as the research object, on the basis of the existing research, the trace of the filament bundle placement is designed. The main work of this paper is as follows: the translation method and the parallel method are two kinds of fiber laying methods, the reason of the gap or overlapping region is analyzed, and the advantages and disadvantages of the two methods are compared synthetically. The basic theory of laminated plate (shell) and the modeling method of sequential response surface are introduced. The quadratic function is selected to create the response surface and the optimal solution of the original problem is obtained by genetic algorithm optimization. The fiber curve trajectory of the laminated plate with variable stiffness is designed. The finite element model of the laminated plate with variable stiffness is established by means of the idea of continuous curve fiber discretization. The effects of fiber locus parameters and geometric parameters on the buckling of laminated plates under uniaxial and biaxial loading are analyzed. The effects of fiber curve locus and geometric parameters on the frequency of laminated plates are discussed. The buckling and frequency characteristics of laminated plates with variable stiffness are optimized by using the sequential response surface method and the T0T 1 optimal solution is obtained. The fiber placement path and layering sequence of variable stiffness (ellipse) cylindrical shells are given, and their finite element models are established in ANSYS, under axial compression, bending moment and torque load, At the same time, the effect of geometrical dimension of cylindrical shell on buckling performance is analyzed. Then the critical buckling coefficient is taken as the target to optimize the buckling characteristics of laminated shells. The results show that the buckling behavior of cylindrical shells can be significantly improved by replacing [45 / 0 / -45 / 90 / -45 / 90] s laminated shells with 45 擄straight line layers with curved fiber layer 胃 under bending moment load, and by controlling the continuous variation of filaments angle, The buckling performance of elliptic cylindrical shells can be improved by changing the circular stiffness of elliptic cylindrical shells to increase the stiffness of the flat parts and decrease the stiffness of the parts with small radius of curvature.
【學(xué)位授予單位】：南昌航空大學(xué)
【學(xué)位級(jí)別】：碩士
【學(xué)位授予年份】：2017
【分類號(hào)】：TB33

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