This study explored the feasibility and potential benefits provided by the addition of through-thickness stitched composite closed-cell foam sandwich structures.
探索了全厚度缝合复合材料闭孔泡沫芯夹层结构低成本制造的工艺可行性及其潜在的结构效益。
The effects of stitching technical parameters such as the stitch thread diameter, stitch step and stitch space on the stitched composite laminates are also analyzed.
研究了缝纫参数(包括缝纫线直径，缝纫针距和行距)对缝纫复合材料层合板屈曲强度的影响。
The alteration of the in-plane elastic properties in laminates caused by stitching was modeled and the in-plane effective tensile strength of the stitched composite laminates was predicted.
旨在研究由缝纫引起的材料弹性性质的变化并对缝纫复合材料层合板面内拉伸强度进行理论预测。
Viscosity of the RFI resin film as a function of curing temperature and time were tested respectively. The mechanical properties of stitched and unstitched composite laminates were evaluated.
测试了改性环氧树脂胶膜熔体粘度对固化温度和时间的依赖性，将缝合与未缝合复合材料层合板试样的基本力学性能进行了试验对比。
The energy method is used to calculate the buckling strength of the stitched composite laminates, and the minimal potential energy is used to calculate that of the unstitched composite laminates.
采用最小势能原理计算了缝纫及未缝纫复合材料层合板的屈曲强度。
To increase the whole strength and stiffness of the composite wing and to lower the manufacturing cost, the main component of the wing is employed with stitched technique.
为了提高复合材料机翼的整体强度和刚度，降低制造成本，机翼的主要结构件采用缝编技术。
Compressive failure tests were carried out on composite laminates and stitched laminates after low velocity impact to study compressive failure mechanisms of laminates after low velocity impact.
对缝纫层合板和无缝纫层合板进行低速冲击后压缩破坏实验，以研究低速冲击后层合板的压缩破坏机理。
Compressive failure tests were carried out on composite laminates and stitched laminates after low velocity impact to study compressive failure mechanisms of laminates after low velocity impact.
对缝纫层合板和无缝纫层合板进行低速冲击后压缩破坏实验，以研究低速冲击后层合板的压缩破坏机理。
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