| 皱褶结构芯格构型的几何设计方法 |
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| 引用本文： | 王志瑾,Khaliulin V I,Skripkin E.皱褶结构芯格构型的几何设计方法[J].南京航空航天大学学报,2002,34(1):6-11. |
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| 作者姓名： | 王志瑾 Khaliulin V I Skripkin E |
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| 作者单位： | 1. 南京航空航天大学航空宇航学院,南京,210016
2. 俄罗斯国立喀山技术大学飞行器系,俄罗斯,420111,喀山,卡尔.马克思大街10号 |
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| 摘 要： | 夹层结构具有较高的抗弯刚度质量比,较好的吸音、隔音、隔热和耐疲劳性能,被广泛应用于航空航天领域。夹层结构的芯材是具有一定抗剪刚度的轻质材料。从理论上讲,可以制造出各种不同构造型式的芯材。但由于工艺方法以及制造成本的限制,目前结构上常用的是由金属或非金属材料制成的六角蜂窝芯材。本文介绍了将平面板材通过按一定有规律的线系进行皱褶,从而形成各种不同构造型式、不同几何尺寸的等高度、变高度或曲面构型等复杂形状的芯材,用以满足各种不同的结构和功能性要求。而且,这种方法具有很好的工艺性。
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| 关 键 词： | 航空 航天 皱褶结构 芯材 几何模型 设计 夹层结构 |
| 文章编号： | 1005-2615(2002)01-0006-06 |
Geometry Design Method of Folded Structure |
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| Khaliulin V I,Skripkin E.Geometry Design Method of Folded Structure[J].Journal of Nanjing University of Aeronautics & Astronautics,2002,34(1):6-11. |
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| Authors: | Khaliulin V I Skripkin E |
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| Abstract: | The sandwich panel construction is broadly used in air and aerospace vehicles due to its high stiffness weight ratio, sound absorber,sound isolate possibility,high thermo isolates performance and good fatigue behavior. Usually the core of sandwich is made from light material with high shear modulus. Theoretically, it is possible to manufacture various forms of cores. But, due to the limitation of technique and cost, currently, only metallic or no metallic hexagon honeycomb is used as core in the sandwich structure. This paper presents a novel method, called "folding method". It is possible to manufacture cores with various geometries required by variety of structure and performance. As viewed from technique, the method is easy to be realized. |
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| Keywords: | sandwich structure folded structure core of sandwich geometry model |
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