D8双泡飞机复合材料Y型接头快速设计工具的验证与确认
Verification and Validation of a Rapid Design Tool for the Analysis of the Composite Y-Joint of the D8 Double-Bubble Aircraft
摘要：
聚合物复合材料接头是增强轻质结构和实现高生态效率运输标准的关键航空航天部件。优化复杂的结构节点是一个迭代过程。需要快速可靠的数值方法来克服高保真有限元（FE）建模的运行时间限制。这项工作提出了一种基于设计工具HyperX的计算效率高的方法。针对D8双泡体机身复合材料Y型接头进行了有限元模型验证和实验验证。结果表明，Y型接头的失效载荷的预测在10%的实验记录的失效载荷。采用基于应力的失效准则，对节点曲率（110° ~ 160°）和蒙皮厚度（16层、24层、32层）对失效载荷预测的影响进行了参数研究。最大失效载荷发生在曲率为130°的Y型接头。预测32层蒙皮Y型接头具有最高的失效载荷。结果证明了快速联合优化分析的适用性，更快，计算效率高的设计。
英文摘要：
Polymer composite joints are critical aerospace components for reinforcing lightweight structures and achieving high eco-efficiency transportation standards. Optimizing complex structural joints is an iterative process. Fast and reliable numerical approaches are needed to overcome the runtime limitations of high-fidelity Finite Element (FE) modeling. This work proposes a computationally efficient approach based on the design tool, HyperX. Verification against FE models and experimental validation are presented for the composite Y-joint in the D8 double bubble fuselage. Results show that the failure load of the Y-joint is predicted within 10% of the experimental failure load recorded. Two parametric studies are performed to study the effects of the curvature of the joint (110° - 160°) and the skin thickness (16ply, 24ply, 32ply) in the failure load predictions using a stress-based failure criterion. The maximum failure load occurred for a Y-joint with 130° curvature. The 32ply skin Y-joint was predicted to have the highest failure load. Results prove the applicability of rapid joint optimization analysis for faster, computationally efficient design.
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