蜂窝夹层结构随面板厚度的逐渐变化会出现不同的屈曲现象。针对连续芯层有限元模型，求出不同面板厚度时结构的屈曲因子，并与经验失稳公式预测值进行对比，两种方法的结果基本吻合。建立考虑芯层几何特征的有限元模型，进行屈曲分析并研究芯层几何参数对结构稳定性的影响。介绍了一种局部屈曲现象——蜂窝壁屈曲，提出了相应的失稳预测分析方法，并与三维有限元分析结果进行比较，验证该方法的正确性。对承受多轴惯性载荷的蜂窝夹层承力筒结构进行稳定性分析，通过改变面板厚度和纵横惯性载荷比，得到一系列有限元解，给出了相关的多轴惯性载荷相关方程。
The buckling factors of honeycomb sandwich structures with fixed size core were obtained with different faceplate thicknesses using homogenization core models. The solutions obtained with the finite element analysis approach were compared with the results from the conventional analytical formulas. The results obtained by two kinds of methods are basically consistent. The finite element models were used in the progress of structural stability analysis, considering the geometry characteristics of the core, and the effect of the eore~s geometry characteristics on the stability problem was discussed. A local instability phenomenon, called cell-wall buckling, was introduced. A prediction analytical approach for the phenomenon was presented, and the results were compared with that of the finite element analysis to validate the proposed approach. The stability problem of satellite sandwich bearing cylinder under the multi- axis inertial loads was studied by the finite element method. The results were obtained with different faceplate thicknesses and different ratios of vertical and horizontal inertial load. The related analysis equation for the multi axis inertial loads was given.
参考文献
| [1] | 徐胜今,孔宪仁,王本利,等.正交异性蜂窝夹层板动、静力学问题的等效分析方法[J].复合材料学报,2000,17(3):92-95. |
| [2] | 唐羽烨,薛明德.蜂窝夹芯板的热学与力学特性分析[J].复合材料学报,2005,22(2):130-136. |
| [3] | 梁森,陈花玲,梁天锡.圆柱形胞元蜂窝夹芯板梁理论的研究[J].复合材料学报,2005,22(2):137-142. |
| [4] | 陈烈民.航天器结构与机构[M].北京:中国科学技术出版社,2005:215-232. |
| [5] | 崔德刚.结构稳定性设计手册[M].北京:航空工业出版社,1996:240-257. |
| [6] | Vinson J R. Optimum design of composite honeycomb sandwich panels subjected to uniaxial compression[J]. AIAA Journal, 1986, 24(10): 104-110. |
| [7] | LeyRP, Lin W, Mbanefo U. Faeesheet wrinkling in sandwich structures, NASA/CR - 1999 - 208994 [R]. Washington: NASA, 1999. |
| [8] | United States Department of Defense. Structural sandwich composites[M]. Washington D C: Department of Defense, 1968. |
| [9] | Vonach W K, Rammerstorfer F G. Wrinkling of thick orthotropic sandwich plates under general loading conditions [J]. Archive of Applied Mechanics, 2000, 70(5): 338-348. |
| [10] | Hadi B K. Wrinkling of sandwich column: Comparison between finite element analysis and analytical solutions [J]. Composite Structures, 2001, 53(4): 477-482. |
| [11] | Fagerberg L. Wrinkling of sandwich panels for marine applications [D]. Stockholm: Royal Institute of Technology, 2003. |
| [12] | Rose C A, Moore D F, Knight N F, et al. Finite element modeling of the buckling response of sandwich panels, AIAA - 2002-1517 [R]. Colorado: AIAA, 2002. |
| [13] | Hohe J. A direct homogenization approach for determination of the stiffness matrix for microheterogeneous plates with application to sandwich panels [J]. Composites Part B: Engineering, 200a, 34(7): 615-626 |
| [14] | Rabczuk T, Kim J Y, Samaniego E, et al. Homogenization of sandwich structures [J]. International Journal for Numerical Methods in Engineering, 2004, 61(7) : 1009-1027. |
| [15] | Leotoing L, Drapier S, Vautrin A. Using new closed-form solutions to set up design rules and numerical investigations for global and local buckling of sandwich beams [J]. Journal of Sandwich Structures and Material, 2004, 6(3): 263-289. |
| [16] | 姚骏,满孝颖,李应典,等.卫星承力筒的结构特点与应用分析[J].电子机械工程,2010,26(3):24-28. |
| [17] | Maly J R, Fowler E C, Biskner A C, et al. Structural models and dynamic measurements of satellite launch adapter structures, AIAA - 2009 - 2695 [R]. California: AIAA, 2009. |
- 下载量()
- 访问量()
- 您的评分：
-
10%
-
20%
-
30%
-
40%
-
50%