复合材料机翼整体成型技术研究  

Research on processing technology of integral composite wing

作　　者：白江波[1,2] 熊峻江[1] 李雪芹[2] 罗楚养[1,2] 张子龙[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国家重点实验室,北京100095

出　　处：《复合材料学报》2011年第3期185-191,共7页Acta Materiae Compositae Sinica

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

摘　　要：对给定外型与尺寸的整体成型复合材料机翼进行了设计、制备及力学性能实验研究。采用有限元分析软件,对空心复合材料机翼进行静力学分析,得到了承载效率与机翼几何尺寸的关系,并确定了最优结构尺寸与复合材料纤维铺层厚度。采用石蜡芯模辅助气囊法成型技术,制备了整体成型复合材料机翼,并进行了三点弯曲实验测定,分析了其破坏机制。三点弯曲实验研究发现,整体成型复合材料机翼的破坏模式为上蒙皮的局部屈曲失效,屈曲后仍有一定的承载能力。The paper seeks to address the techniques of structural optimization design,manufacturing and experimental measurement of mechanical properties for integral composite wing with the specific dimension and configuration.By using finite element analysis（FEA） code,the numerical simulation on static strength of hollow composite wing was conducted to obtain the relationship between load-carrying efficiency and geometric dimension.From the FEA results,the optimized dimension of wing and ply thickness for stacking fibre were determined.An integral composite wing was processed by using the processing technique incorporating balloon-forming method and paraffin core mould.The three-point bending test was performed to verify the mechanical properties of wing,and the failure mechanism was discussed from experimental observation.It is found that the main failure mode is local buckling occurring on upper surface of composite wing,and the wing with local buckling is still capable of carrying a load.

关 键 词：复合材料机翼 有限元 石蜡芯模 气囊法成型 三点弯曲 局部屈曲 

分 类 号：TB330.1[一般工业技术—材料科学与工程] V258[航空宇航科学与技术—航空宇航制造工程]