航空铝合金板坯成形极限图的建立

S. I. Feoktistov, I. Andrianov
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Logarithmic deformations with the property of additivity were used to account for large deformations. The construction of the diagram of the limit deformations was carried out in the formulation of the deformation theory of plasticity. The issue of constructing a diagram of limit deformations was considered on the basis of the positivity criterion of the loading force derivative. In the area of negative values of the smallest major deformations, the Hill criterion was used to construct the limit deformation curve, and in the area of positive values of the smallest major logarithmic deformations, the Swift criterion was used. When constructing the limit deformation diagram, a power approximation of the hardening rule was used.Results. The curves of limiting deformations for the following aviation alloys were obtained: AMg6, D16AT, AMg2M, 1201-T, AMcM. 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引用次数: 0

摘要

介绍。冲压飞机制造的现代发展与板材毛坯极限能力的评估是密不可分的。然而,航空铝合金坯料的无缺陷成形问题还没有得到充分的研究。这个问题的重要性是由于铝合金经常被用于制造航空用途的薄壁产品。在成形过程的实施过程中,可能出现各种缺陷,特别是波纹或不可接受的变薄。在这方面,工作的目的是构建基本航空合金的极限变形图,并对这些材料的极限变形曲线进行比较分析。材料与方法。采用具有可加性的对数变形来解释大变形。在塑性变形理论的表述中,进行了极限变形图的构造。基于载荷力导数的正性准则,考虑了极限变形图的构造问题。在最小主要变形为负值的区域,采用Hill准则构建极限变形曲线,在最小主要对数变形为正值的区域,采用Swift准则构建极限变形曲线。在构造极限变形图时,采用了硬化规律的幂次近似。得到了AMg6、D16AT、AMg2M、1201-T、AMcM等航空合金的极限变形曲线。通过对安全成形区域的对比分析,比较了缩颈起始变形值及其对坯料极限变形曲线位置变化的影响:缩颈成形变形越大,极限变形曲线位置越高。介绍了基勒极限变形图的概念。提出了基于薄板试件拉伸试验结果的Hill-Swift准则的构建方法。讨论和结论。基于所构建的航空合金AMg-6、D16AT、AMg2M、1201-T、AMcM的极限变形曲线,得到了以下结果:AMg2M合金的安全成形面积最大,1201-T合金的安全成形面积最小。这可以用颈部形成初期相对变形的差异来解释。所进行的研究使评估基本航空铝合金薄壁毛坯无缺陷成形的可能性成为可能。利用所构造的极限变形图,可以预测板坯成形过程中断裂的出现。
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Construction of Forming Limit Diagram for Sheet Blanks from Aviation Aluminum Alloys
Introduction. The modern development of stamping aircraft manufacturing is inextricably linked with the assessment of the limiting capabilities of sheet blanks. However, the issue of defect-free forming of blanks made of aviation aluminum alloys is understudied. The importance of this issue is due to the fact that aluminum alloys are often used in the manufacture of thin-walled products for aviation purposes. During the implementation of shaping processes, various defects may appear, specifically, corrugation or unacceptable thinning. In this regard, the objective of the work was to construct a diagram of the limit deformations of the base aviation alloys and to conduct a comparative analysis of the limit deformation curves for these materials.Materials and Methods. Logarithmic deformations with the property of additivity were used to account for large deformations. The construction of the diagram of the limit deformations was carried out in the formulation of the deformation theory of plasticity. The issue of constructing a diagram of limit deformations was considered on the basis of the positivity criterion of the loading force derivative. In the area of negative values of the smallest major deformations, the Hill criterion was used to construct the limit deformation curve, and in the area of positive values of the smallest major logarithmic deformations, the Swift criterion was used. When constructing the limit deformation diagram, a power approximation of the hardening rule was used.Results. The curves of limiting deformations for the following aviation alloys were obtained: AMg6, D16AT, AMg2M, 1201-T, AMcM. According to the comparative analysis of the areas of safe forming, the values of deformations of the beginning of necking and their influence on the change in the position of the curve of the limiting deformation of blanks were compared: the greater the deformation of the neck formation, the higher the position of the curve of the limiting deformations. The concept of the Keeler's limit deformation diagram was described. Approaches to the construction of the Hill-Swift criteria used on the basis of the results of tensile testing of sheet specimens were presented.Discussion and Conclusions. Based on the constructed curves of limiting deformations for aviation alloys, AMg-6, D16AT, AMg2M, 1201-T, AMcM, the following has been found. AMg2M alloy has the largest area of safe forming, 1201-T alloy has the smallest one. That is explained by the difference in relative deformations of the beginning of neck formation. The conducted research made it possible to evaluate the possibilities of defect-free forming of thin-walled blanks made of basic aviation aluminum alloys. The use of the constructed diagrams of limiting deformation will provide predicting the appearance of breaks in the process of forming sheet blanks.
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