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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%。
In order to achieve the design requirement of wingtip torsional increment and to achieve the purpose of improving the aerodynamic characteristics of aircraft, the paper takes advantage of the torsional and torsional coupling characteristics of the composite materials, studies the non-balanced composite design and technology of composite materials, Airfoil composite structure bending and torsional coupling design of engineering solutions, and carried out comparative experimental study. The experimental results show that after the tailored design, the washing effect of simulated wing box section is obvious, and the increment of torsional angle of wing tip is reduced by 10% -45% under different loads.