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首页> 美国卫生研究院文献>Materials >High Temperature Mechanical Properties of a Vented Ti-6Al-4V Honeycomb Sandwich Panel
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High Temperature Mechanical Properties of a Vented Ti-6Al-4V Honeycomb Sandwich Panel

机译：通风Ti-6AL-4V蜂窝夹芯板的高温机械性能

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摘要

For aerospace applications, honeycomb sandwich panels may have small perforations on the cell walls of the honeycomb core to equilibrate the internal core pressure with external gas pressure, which prevent face-sheet/core debonding due to pressure build-up at high temperature. We propose a new form of perforation on the cell walls of honeycomb sandwich panels to reduce the influence of the perforations on the cell walls on the mechanical properties. In this paper, the high temperature mechanical properties of a new vented Ti-6Al-4V honeycomb sandwich panel were investigated. A vented Ti-6AL-4V honeycomb sandwich panel with 35Ti-35Zr-15Cu-15Ni as the filler alloy was manufactured by high-temperature brazing. The element distribution of the brazed joints was examined by means of SEM (scanning electron microscopy) and EDS (energy-dispersive spectroscopy) analyses. Compared to the interaction between the face-sheets and the brazing filler, the diffusion and reaction between the honeycomb core and the brazing filler were stronger. The flatwise compression and flexural mechanical properties of the vented honeycomb sandwich panels were investigated at 20, 160, 300, and 440 °C, respectively. The flatwise compression strength, elastic modulus, and the flexural strength of the vented honeycomb sandwich panels decreased with the increase of temperature. Moreover, the flexural strength of the L-direction sandwich panels was larger than that of the W-direction sandwich panels at the same temperature. More importantly, the vented honeycomb sandwich panels exhibited good compression performance similar to the unvented honeycomb sandwich panels, and the open holes on the cell walls have no negative effect on the compression performance of the honeycomb sandwich panels in these conditions. The damage morphology observed by SEM revealed that the face-sheets and the brazing zone show ductile and brittle fracture behaviors, respectively.
机译：对于航空航天应用，蜂窝夹层面板可以在蜂窝芯的电池壁上具有小穿孔，以使内部芯压力与外部气体压力平衡，这防止由于高温压力堆积而导致的面板/核心剥离。我们在蜂窝夹层面板的细胞壁上提出了一种新的穿孔，以减少穿孔在机械性能上的细胞壁上的影响。本文研究了新的通风Ti-6AL-4V蜂窝夹层板的高温力学性能。具有35Ti-35ZR-15CU-15NI作为填料合金的通风Ti-6AL-4V蜂窝夹层板是通过高温钎焊制造的。通过SEM（扫描电子显微镜）和EDS（能量分散光谱）分析检查钎焊接头的元素分布。与面板和钎料之间的相互作用相比，蜂窝芯和钎料之间的扩散和反应更强。在20,160,300和440°C中研究了通气蜂窝夹层板的平坦压缩和弯曲力学性能。随着温度的增加，出通风蜂窝夹层板的扁平压缩强度，弹性模量和弯曲强度降低。此外，L方向夹层板的弯曲强度大于相同温度的W方向夹层板的弯曲强度。更重要的是，通风蜂窝夹层面板表现出类似于未辩护的蜂窝夹层板的良好压缩性能，并且细胞壁上的开孔对这些条件下蜂窝夹层板的压缩性能没有负面影响。 SEM观察到的损伤形态透露，脸部和钎焊区分别显示出韧性和脆性断裂行为。

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