复合材料无矩叠层板铺层优化设计——按静力破坏条件

 飞机翼面结构受力盒段的上下壁板若采用纤维增强复合材料叠层板则经常可简化为无矩叠层板;本文介绍这种叠层板按静力破坏条件的一种铺层优化设计方法。本法所用的数学工具为拉格朗日乘子法,采用的静力破坏条件为Hill-Tsai判据或Norris判据。对于铺层优化设计要用的公式进行了推导并且为了便于应用电子计算机对所得的公式进行了相应的改造。 关于叠层板极限强度的确定,文中也作了较仔细的探讨。为了具体说明本法的解题步骤以及如何选出铺层设计的优化方案举出了一个数例。文章的最后对几个技术问题进行了简要的讨论。 在结构打样设计阶段,对于翼面结构中处于拉伸或压缩受载（在不发生屈曲失稳破坏的条件下）情况下的复合材料壁板,本法可作为其铺层优化设计的一种工程方法。

THE OPTIMUM DESIGN OF NON-MOMENT LAMINATED COMPOSITE PLATE -According to static failure strength condition

When the upper and/or lower panels of the loading box of the aircraft wing or tail are made of the fiber reinforced composite laminates, they can frequently be simplified as a non-moment plate. This paper introduces an optimum design （i. e. minimum weight design） procedure of the laminated plate on static failure strength condition. The mathematical tool used in the procedure is Lagrangian Multiplier method, and the static failure strength condition is adopted as Hill-Tsai criteria or Norris criteria.The formulae for optimum design have been not only derived, but also reformed to be convenient for the computer. How to establish the ultimate strength of laminates is discussed in detail. An example, illustrating the solution procedure and how to select the optimum scheme of lamination design, is presented in the paper. Some technical problems are briefly discussed in the last part.At the stage of the preliminary structural design, this procedure can be considered as an engineering method of lamination optimum design for the loading panel of laminated composite, which works under tension or compression （assuming that the buckling failure would not occur）.