Buckling-optimized variable stiffness laminates for a composite fuselage window section
Buckling-optimized variable stiffness laminates for a composite fuselage window section
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发表时间：
2012
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通讯作者：
W. V. D. Brink;W. Vankan;R. Maas
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作者：
W. V. D. Brink;W. Vankan;R. Maas
与金属相比，复合材料提供了潜力，因为最终结构可以根据各向异性材料特性进行定制。在当今航空航天领域的大多数薄平面结构中，由于使用的是传统的准各向同性层合板，复合材料的这些各向异性特性没有得到充分利用。现代自动纤维铺放制造能力使可变刚度层压板的引入更大规模。本文提出了一种两步变刚度设计方法。首先确定最佳纤维取向。从这些纤维取向，物理复合纤维丝束的衍生。除了屈曲优化，如本文所述，变刚度层合板也可以用于例如改进载荷传递和变形结构。
Composite material offers potential compared to metals in the way the final structure can be tailored with the anisotropic material properties. In most thin planar structures in aerospace today these anisotropic properties of composite material are not fully exploited because traditional quasi isotropic laminates are used. Modern Automated Fiber Placement manufacturing capabilities enable the introduction of variable stiffness laminates on a larger scale. In this paper a two-step variable stiffness design approach is proposed. First the optimal fiber orientations are determined. From these fiber orientations the physical composite fiber tows are derived. Besides buckling optimization, as addressed in this paper, variable stiffness laminates can also be used e.g. for improvement of load transfer and morphing structures.