为实现机翼翼尖扭角增量的设计要求，达到改善飞机气动弹性特性的目的，利用复合材料的弯扭耦合特性，着重对复合材料非均衡铺层设计和工艺技术进行了研究，提出了对翼面复合材料结构弯扭耦合特性进行设计的工程解决方法，并开展了对比试验研究。试验结果表明，经剪裁设计后，模拟机翼盒段外洗效果明显，在不同载荷作用下，翼尖扭角增量降低10％～45％。
Based on the bend/twist coupling characteristics of composite materials, the design and process technology of unbalanced composite material laminating have been studied to achieve the design requirements of wingtip twist angle increment and improve the aero-elastic characteristics of aircraft. An engineering solution was developed to design the twist coupling characteristics for composite wing structure, and contrast experiments have been carried out. The test results show that the effectiveness of wash-out of the wing box is considerable after tailoring design and the twist angle increment of wingtip decreases by 10%-45 % under different loadings.
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