GLARE層板滾彎成形的理論分析與試驗(yàn)研究
發(fā)布時(shí)間：2018-10-23 08:47
【摘要】：作為第二代纖維金屬層板,GLARE層板綜合了復(fù)合材料和金屬材料的各種優(yōu)異性能,目前該類層板的研究熱點(diǎn)主要集中于制備工藝、復(fù)雜構(gòu)件成形方法以及服役性能評價(jià)等。因此,本文針對GLARE層板的滾彎成形理論與工藝技術(shù)開展了系統(tǒng)地研究分析,為GLARE層板在大型飛機(jī)上的應(yīng)用提供理論依據(jù)和工程指導(dǎo)。首先,通過試驗(yàn)研究了GLARE層板的基本成形性能。結(jié)果可知,采用n yσ=σ+Kε本構(gòu)模型來擬合真實(shí)應(yīng)力-應(yīng)變曲線,其擬合結(jié)果最優(yōu)。GLARE 2A層板的抵抗拉伸變形能力最強(qiáng),很難產(chǎn)生厚向變形,因此其壓延成形性能較差。在彎曲變形過程中,GLARE 6A層板的相對彎曲角最小,并且GLARE 6A層板的彎曲回彈量最小,表現(xiàn)出良好的彎曲成形性能。其次,通過理論分析建立了GLARE層板滾彎成形的解析模型。采用Hill屈服準(zhǔn)則和指數(shù)強(qiáng)化模型來描述各向異性的鋁合金板材,分析計(jì)算了彎曲成形過程中GLARE層板的應(yīng)力應(yīng)變分布、彎矩大小以及理論回彈半徑和回彈角,建立了層板滾彎成形的解析模型。通過試驗(yàn)驗(yàn)證了解析模型的準(zhǔn)確性,表明所建立的解析模型具有一定的適用性。隨后,通過試驗(yàn)研究分析了上輥下壓量、纖維鋪層方式以及層板結(jié)構(gòu)三個參數(shù)對其滾彎回彈規(guī)律的影響。研究結(jié)果表明,上輥下壓量越大,GLARE層板的回彈越小,并且上輥下壓量與層板的彎曲成形半徑之間的關(guān)系曲線符合冪函數(shù)關(guān)系。保持上輥下壓量相同情況下,GLARE2A層板的回彈量最大,GLARE 3層板次之,GLARE 6A層板最小。GLARE層板的回彈量是隨著結(jié)構(gòu)的增加而逐漸減小,并且減小的幅度趨向于穩(wěn)定。另外,采用腐蝕去層法分析了滾彎成形后GLARE層板的殘余應(yīng)力分布情況,分析結(jié)果表明,層板的外表面及其整個鋁合金層均處于壓應(yīng)力狀態(tài),但是不同類型GLARE層板鋁合金層的殘余應(yīng)力變化規(guī)律并不明顯。最后,利用SEM對滾彎成形后的GLARE層板損傷失效特征進(jìn)行了觀察分析,得到了層板的臨界下壓量和臨界成形曲率半徑。結(jié)果表明,當(dāng)上輥下壓量達(dá)到12 mm時(shí),玻璃纖維達(dá)到極限應(yīng)變,層板發(fā)生損傷失效,以GLARE 2A層板為研究對象,由此可確定,在滾彎成形過程中,臨界上輥下壓量為11 mm,對應(yīng)的臨界彎曲曲率半徑為172.47 mm。當(dāng)上輥下壓量達(dá)到12 mm時(shí),三種纖維鋪層方式的GLARE層板均發(fā)生一定程度的損傷失效,其失效形式主要表現(xiàn)為樹脂基體擠壓破壞、基體開裂以及纖維斷裂,但都沒有出現(xiàn)界面分層現(xiàn)象。當(dāng)GLARE層板從3/2結(jié)構(gòu)依次增大為4/3、5/4、6/5結(jié)構(gòu)時(shí),層板的損傷失效程度也隨之變大。
[Abstract]:As the second generation fibrous metal laminates, GLARE laminates integrate various excellent properties of composite materials and metal materials. At present, the research focus of this kind of laminates is mainly on the preparation process, the forming methods of complex components and the evaluation of service performance. Therefore, in this paper, the theory and technology of roll bending forming of GLARE laminates are systematically studied and analyzed, which provides theoretical basis and engineering guidance for the application of GLARE laminates in large aircraft. Firstly, the basic formability of GLARE laminates was studied by experiments. The results show that the true stress-strain curve is fitted by the constitutive model of ny 蟽 = 蟽 K 蔚, and the fitting result is optimal. The GLARE 2A laminate has the strongest resistance to tensile deformation and is difficult to produce thick deformation, so the forming property of GLARE 2A laminate is poor. In the process of bending deformation, the relative bending angle of GLARE 6A laminates is the smallest, and the flexural springback of GLARE 6A laminates is the least, which shows good bending formability. Secondly, the analytical model of GLARE sheet roll forming is established by theoretical analysis. Hill yield criterion and exponential strengthening model are used to describe anisotropic aluminum alloy sheet. The stress and strain distribution, bending moment, theoretical springback radius and springback angle of GLARE laminates during bending forming are analyzed and calculated. The analytical model of laminate rolling forming is established. The accuracy of the analytical model is verified by experiments, which shows that the established analytical model is applicable to some extent. Then, the influence of three parameters, such as the pressure of upper roll, fiber layer and laminate structure, on the springback rule of roll bending is analyzed. The results show that the higher the pressure is, the smaller the springback of the GLARE laminate is, and the curve between the roll down pressure and the bending radius of the laminate is in accordance with the power function. When the upper roll pressure is the same, the springback of GLARE2A laminates is the largest, that of GLARE 3 laminates is the second, and that of GLARE 6A laminates is the smallest. The springback of GLARE laminates decreases gradually with the increase of structure, and the decreasing amplitude tends to be stable. In addition, the residual stress distribution of GLARE laminates after roll forming is analyzed by corrosion delamination method. The results show that the external surface of the laminate and its whole aluminum alloy layer are in the state of compressive stress. However, the variation of residual stress in different types of GLARE laminate aluminum alloy layer is not obvious. Finally, SEM was used to observe and analyze the damage failure characteristics of GLARE laminates after rolling forming, and the critical compression and curvature radius of the laminates were obtained. The results show that when the pressure of top roll reaches 12 mm, the glass fiber reaches the limit strain and the laminate is damaged and invalidated. Taking the GLARE 2A laminate as the research object, it can be determined that in the process of rolling forming, The critical bending curvature radius corresponding to the critical roll down pressure of 11 mm, is 172.47 mm.. When the pressure of the top roller reaches 12 mm, the GLARE laminates with three kinds of fiber laminates have a certain degree of damage and failure. The main failure forms are extruding failure of resin matrix, cracking of matrix and fiber fracture. However, there is no phenomenon of interface delamination. When the structure of GLARE laminates increases from 3 / 2 to 4 / 3 / 5 / 4 / 5, the damage failure degree of the laminates also increases.
【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
本文編號：2288733
[Abstract]:As the second generation fibrous metal laminates, GLARE laminates integrate various excellent properties of composite materials and metal materials. At present, the research focus of this kind of laminates is mainly on the preparation process, the forming methods of complex components and the evaluation of service performance. Therefore, in this paper, the theory and technology of roll bending forming of GLARE laminates are systematically studied and analyzed, which provides theoretical basis and engineering guidance for the application of GLARE laminates in large aircraft. Firstly, the basic formability of GLARE laminates was studied by experiments. The results show that the true stress-strain curve is fitted by the constitutive model of ny 蟽 = 蟽 K 蔚, and the fitting result is optimal. The GLARE 2A laminate has the strongest resistance to tensile deformation and is difficult to produce thick deformation, so the forming property of GLARE 2A laminate is poor. In the process of bending deformation, the relative bending angle of GLARE 6A laminates is the smallest, and the flexural springback of GLARE 6A laminates is the least, which shows good bending formability. Secondly, the analytical model of GLARE sheet roll forming is established by theoretical analysis. Hill yield criterion and exponential strengthening model are used to describe anisotropic aluminum alloy sheet. The stress and strain distribution, bending moment, theoretical springback radius and springback angle of GLARE laminates during bending forming are analyzed and calculated. The analytical model of laminate rolling forming is established. The accuracy of the analytical model is verified by experiments, which shows that the established analytical model is applicable to some extent. Then, the influence of three parameters, such as the pressure of upper roll, fiber layer and laminate structure, on the springback rule of roll bending is analyzed. The results show that the higher the pressure is, the smaller the springback of the GLARE laminate is, and the curve between the roll down pressure and the bending radius of the laminate is in accordance with the power function. When the upper roll pressure is the same, the springback of GLARE2A laminates is the largest, that of GLARE 3 laminates is the second, and that of GLARE 6A laminates is the smallest. The springback of GLARE laminates decreases gradually with the increase of structure, and the decreasing amplitude tends to be stable. In addition, the residual stress distribution of GLARE laminates after roll forming is analyzed by corrosion delamination method. The results show that the external surface of the laminate and its whole aluminum alloy layer are in the state of compressive stress. However, the variation of residual stress in different types of GLARE laminate aluminum alloy layer is not obvious. Finally, SEM was used to observe and analyze the damage failure characteristics of GLARE laminates after rolling forming, and the critical compression and curvature radius of the laminates were obtained. The results show that when the pressure of top roll reaches 12 mm, the glass fiber reaches the limit strain and the laminate is damaged and invalidated. Taking the GLARE 2A laminate as the research object, it can be determined that in the process of rolling forming, The critical bending curvature radius corresponding to the critical roll down pressure of 11 mm, is 172.47 mm.. When the pressure of the top roller reaches 12 mm, the GLARE laminates with three kinds of fiber laminates have a certain degree of damage and failure. The main failure forms are extruding failure of resin matrix, cracking of matrix and fiber fracture. However, there is no phenomenon of interface delamination. When the structure of GLARE laminates increases from 3 / 2 to 4 / 3 / 5 / 4 / 5, the damage failure degree of the laminates also increases.
【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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