采用基于水溶性型芯的RTM成型技术制备了整体化的复合材料翼盒，并对翼盒进行了自由振动模态试验；采用三维壳单元，建立了翼盒固有模态及稳定性有限元分析模型，该模型分析的翼盒固有模态与试验结果吻合很好，验证了有限元模型的有效性；为研究翼盒固有模态及稳定性的铺层效应，采用该模型分析计算了4种铺层方案的翼盒的固有模态及稳定性。研究结果表明：对称铺层蒙皮有利于提高翼盒轴向压缩与轴向扭转屈曲载荷及固有频率，而不利于面外弯曲和弯扭组合情况；腹板减薄和增加腹板45°铺层均不利于提高，甚至会大幅度降低屈曲载荷及固有频率，弯扭组合加载最容易导致失稳。
Based on water-soluble mandrel, the integrated composite wing box was fabricated via resin transfer molding （RTM）. The test of natural modal of wing box was conducted. The finite element （FE） models for modal and buckling analysis of wing box were generated by using 3D shell element to investigate the stacking sequence effect on the natural modal and bucking properties. The calculations of natural modal are consistent well with the experiments, validiting the FE model proposed in the paper. The FE model was applied to simulate the natural modal and stability of wing box with four different layups. The results show that symmetrical layers of the skin have significant beneficial effects on natural frequency and buckling loads of wing box under axial compression and torsion, in contrast, have distinct adverse effects on those under the bending and combination of bending and torsion. In addition, the rigidity of web has an apparent beneficial effect on the buckling load and natural frequency of wing box, whereas the increasing of 45° plies or the decreasing of the thickness of web would reduce buckling load and natural frequency.
参考文献
| [1] | 杨乃宾.新一代大型客机复合材料结构[J].航空学报,2008,29(3):596-609. |
| [2] | Rehfield L W. A refined simple model for tailoring box beams with composites [C]//42nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. Seattle: AIAA, 2001: 25112 |
| [3] | 张桂江.飞行器复合材料结构弹性刚度剪裁优化设计技术研究[D].西安:西北工业大学,2006. |
| [4] | Haddadpour H, Kouchakzadeh M A, Shadmehri F. Aeroelastic instability of aircraft composite wings in an incompressible flow [J]. Composite Structures, 2008, 83(1):93-99. |
| [5] | Romeo G, Frulla G, Busto M. Nonlinear angle of twist of advanced composite wing boxes under pure torsion [J]. Journal of Aircraft, 1994, 31(6) : 1297-1302. |
| [6] | 陈玲玲.典型机翼盒段静力破坏过程的数值仿真[D].南京:南京航空航天大学,2008. |
| [7] | 张永涛.某型飞机机翼盒段耐久性分析[D].南京:南京航空航天大学,2008. |
| [8] | Icardi U, Ferrero L. Preliminary study of an adaptive wing with shape memory alloy torsion actuators[J]. Materials Design, 2009, 30(10): 4200-4210. |
| [9] | Stiftinger M A, Skrna- Jakl I C, Rammerstorfer F G. Buckling and postbuckling investigations of imperfect curved stringer-stiffened composite shells: Part B--Computational investigations [J]. Thin-Walled Structures, 1995, 23(1/2/3/ 4) : 339-350. |
| [10] | Skrna-Jakl I C, Stiftinger M Numerical investigations of an composite wing torsion box- A, Rammerstorfer F G. imperfect stringer stiffened An analysis concept [J].Composites: Part B, 1996, 27(1): 59-69. |
| [11] | Ovesy H R, Assaee H. Buckling characteristics of some composite stiffened boxes under longitudinal compression or bending using finite strip approach [C]//44th AIAA/ASME/ASCE/AHS Structures, Structural Dynamics, and Materials Conference. Norfolk: AIAA, 2003: 1791 |
| [12] | De Baets P W G, Battoo R S, Mavris D N. Aeroelastic analysis of a composite wingbox with varying root flexibility [ C ] // 41st AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference and Exhibit. Atlanta: AIAA, 2000: 1623 |
| [13] | 邵骞.复合材料结构强度分析与试验研究[D].西安:西北工业大学,2005. |
| [14] | Kong C W, Park J S, Cho J H, et al. Testing and analysis of downscaled composite wing box [J]. Journal of Aircraft, 2002, 39(3) : 480-485. |
| [15] | 刘兵山,燕瑛,钱卫,等.复合材料机翼盒段的设计、模态分析和试验[J].北京航空航天大学学报,2003,29(11):1026-1028. |
| [16] | 益小苏.先进复合材料技术研究与发展[M].北京:国防工业出版社,2006:66-76. |
| [17] | 邱婧婧,段跃新,梁志勇.RTM工艺参数对树脂充模过程影响的模拟与实验研究[J].复合材料学报,2004,21(6):70-74. |
| [18] | 戴福洪,张博明,杜善义,等.复杂形状三维薄壁构件RTM制造工艺注模过程模拟[J].复合材料学报,2004,21(2):87-91. |
| [19] | 白江波,熊峻江,程序,等.RTM成型复合材料T型接头工艺参数优化与力学性能实验研究[J].复合材料学报,2009,26(3):13-14. |
| [20] | 罗楚养,熊峻江,益小苏,等.基于水溶性型芯的RTM成型的整体化复合材料翼盒研制[J].复合材料学报,2011,28(3):217-222. |
| [21] | 益小苏,王岭,仝建峰,等.一种水溶性模芯的制备方法:中国,200710306024.X[P].2008-07-30 |
- 下载量()
- 访问量()
- 您的评分：
-
10%
-
20%
-
30%
-
40%
-
50%