整体成型复合材料模型机翼设计、制造与验证  

Design,Manufacturing and Testing of Composite Wing Model via Integral Forming Process

作　　者：罗楚养[1,2] 益小苏[2] 李伟东[2] 周玉敬[2] 朱亦钢[2] 刘刚[2] 

机构地区：[1]北京航空航天大学交通科学与工程学院,北京100191 [2]北京航空材料研究院先进复合材料重点实验室,北京100095

出　　处：《航空材料学报》2011年第4期56-63,共8页Journal of Aeronautical Materials

基　　金：国家自然科学基金资助项目(E050603);航空科学基金资助项目(20095251024)

摘　　要：根据给定的外形设计了四种不同结构形式的复合材料模型机翼,通过对所采用树脂基体的化学流变特性的研究,确定其最佳固化工艺条件。采用整体成型技术制备了四种全复合材料模型机翼,并进行了三点弯曲试验。结果表明,工字梁结构形式的模型机翼具有最高的载荷重量比,其次为C型梁机翼,而蒙皮-夹芯机翼的载荷重量比最小。其中,蒙皮-夹芯模型机翼在测试中表现为加载点上蒙皮压缩破坏;蒙皮-加筋机翼则表现为支点处的剪切破坏;梁式结构机翼均表现为支点与加载点中间的前缘剪切破坏。采用有限元分析模型机翼的强度与破坏过程,其结果与试验结果吻合良好。Four different structure wings were designed according to the given configuration.Based on the optimized curing process of the resin,the four composite wing models were manufactured via integral forming technique.The three point bending test results show that the I-beam wing has the highest load-carrying efficiency,then the following is the C-beam wing.The skin-foam wing has the minimum load-carrying efficiency.The failure of skin-foam wing is caused by compression failure of upper skin at loading point,while the skin-stiffened wing is failures from the shear break of support point.The C-beam and I-beam structure wings both have shear failures at the wing leading edge between loading point and support point.The finite element analysis（FEA） result is consistent well with those of experiment.

关 键 词：复合材料机翼 整体成型 三点弯曲 有限元分析 泡沫夹芯 

分 类 号：TB332[一般工业技术—材料科学与工程]