A method is presented to fix on the location of stiffness-center axis of a composite wing by use of finite element method. A series of finite element models of composite wing are set up to analyze the influencing factors on stiffness-center axis. The result shows it has greater influence on the location of stiffness-center axis with change of mass distribution, aspect ratio and swept-back angle, and relatively smaller influence with change of the location of spar, lay-up form, lay-up ratio and lay-up sequence. It provides some references to design the composite wing.%采用有限元分析方法,确定复合材料机翼中刚心轴线的位置.建立一系列的复合材料机翼有限元模型,对影响刚心轴线位置的因素进行具体分析.结果表明,质量分布、展弦比和后掠角的变化对机翼刚心轴线位置有较大的影响,前后梁的位置、铺层形式、铺层比例和铺层顺序的变化对机翼刚心轴线位置的影响相对较小.本研究为复合材料机翼的设计提供一定的参考.
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