Given a design requirement for configuration , we establish the model of the light composite wing with foam sandwich structure .Firstly, we use the thin-wall beam theory to calculate respectively the distributions of nor-mal stress and shear stress at the largest sections of wing structures with single closed chamber and triple closed chamber when they are under three-point bending load .Then, we use the ABAQUS software which is suitable for the kind of wing model to simulate the loading of the wing model; we also did experiments on the loading of the wing model we made .The simulation results and experiments results , given in Figs.7 and 8 and Table 4, show that they agree well , indicating that the simulation is effective .We use damage load as the maximum bearing capacity of the composite wing and its ratio of loading to mass as the structural efficiency to design four types of composite wing and ten wing schemes .We simulate the nine wing schemes and do the three-point bending load damage experiments on the wing model we made .The comparison of the simulation and experimental results , given in Table 8, show preliminarily that:(1) the composite wing with triple closed chamber satisfies design requirements better than that with single closed chamber;( 2) the former with ribs added can enhance its bearing capacity and structural effi-ciency .%在给定外形尺寸的设计要求下，提出1种全复合材料轻型机翼结构设计模型。首先，采用薄壁工程梁理论，对2种机翼剖面构型（单闭室和三闭室）在三点弯曲载荷条件下，进行了正应力与剪应力分布计算。并对初始设计方案机翼进行了三点弯曲载荷下的加载破坏试验，随后选取了ABAQUS软件中1种适合于此类机翼模型的数值模拟方法，建立了机翼结构数值分析模型，数值模拟结果与试验结果吻合良好。以破坏载荷作为衡量机翼结构极限承载能力的指标，以载荷/质量比作为衡量机翼结构效率的指标，设计了4种结构类型，10个方案的全复合材料机翼结构模型，并对每种方案进行了有限元分析。最后提出了1种在三点弯曲试验条件下，满足设计要求，并且承载能力强、结构效率高的全复合材料轻型机翼结构设计方案。
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