无人机全复合材料机翼结构设计与试验验证

为提高全复合材料机翼的有效载荷与机翼质量的比值(载荷/质量比),提出了一种预测全复合材料机翼极限载荷的有限元模拟方法,并建立了提高机翼结构效率的结构设计方案。首先,基于薄壁工程梁理论,对全复合材料机翼进行了理论分析,并对全复合材料机翼的结构形式与铺层形式进行了初始设计;然后,基于初始机翼的试验数据,利用ABAQUS建立了4种不同的有限元模型,通过对比得到了最佳数值模拟方法;接着,建立了14种结构布局形式,并为每种结构形式赋予不同的铺层方案,形成了117个机翼设计方案,对比了各个结构形式的载荷/质量比以及工艺因素;最后,制造了全复合材料机翼并进行了试验验证。结果表明:双工字梁结构为最佳机翼结构布局形式,具有较高的承载效率;模拟载荷与试验值之间的相对误差仅为1.91%,验证了有限元模型的正确性;机翼的载荷/质量比达到了24.17 N/g,相对于初始设计提升了30.65%。所得结论表明设计方法有效。 

Structural design and test verification of all-composite wing for unmanned aerial vehicle

In order to improve the ratio of effective load to wing mass (load/mass ratio)of all-composite wing,a finite element simulate approach was proposed to predict the ultimate load of all-composite wing,and the structural design framework which can raise the structural efficiency of wing was established.First,based on the thin-walled engineering beam theory,theoretical analysis was conducted on all-composite wing,and the initial design of struc-ture form and lay-ups form for all-composite wing was preceded.Then,based on the testing data of initial wing, four kinds of different finite element models were built using ABAQUS,and the best numerical simulate approach was obtained by contrast.After that,fourteen kinds of structure configuration forms were established and each structure form were given with different lay-up plans,thus one hundred and seventeen design plans for wing were formed,the load/mass ratios and manufacture factors of each structure form were contrasted.Finally,the all-com-posite wing was manufactured and test verification was conducted.The results show that double I-beam structure is the best structure configuration form of wing,which has relatively high load bearing efficiency.The relative error between simulated load and testing value is only 1.9 1%,which verifies the correctness of finite element model.The load/mass ratio of wing reaches 24.17 N/g,which is 30.65% higher comparing with that of the initial design.The conclusions obtained show that the design approach is valid.