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Experimental Study on Damage Characteristics of CFRPs/Aluminum Honeycomb Sandwich Structure Impacted by Ultra-High Speed Under High and Low Temperatures

机译:高温下超高速影响CFRPS /铝蜂窝夹层结构损伤特性的实验研究

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With the rapid development of material science, the original aluminum alloy shield structure of spacecraft has been gradually replaced by sandwiched structure of carbon fiber reinforced resin matrix composite structure with aluminum honeycomb. In order to reveal the damage characteristics induced by debris impacting on shield structure of spacecraft and aiming at the engineering requirements that spacecraft undergo alternately high and low temperature environment during on-orbit operation, CFRPs/aluminum honeycomb core sandwich shield structure is used as the impact object. The damage characteristics of 2A12 aluminum projectile impacting on CFRPs/aluminum honeycomb sandwich structure with different aluminum honeycomb arm lengths at different impact velocities are studied by using the high and low temperature system for the target and the loading system of two-stage light gas gun. The experimental results show that the arm lengths of aluminum honeycomb have little effect on the perforation area of front and rear surfaces of CFRPs/aluminum honeycomb sandwich structure at high temperature, but the impact speed has a great effect on the perforation areas of front and rear surfaces of rear panels. The lower the impact speed is, the smaller the perforation diameter is. The deformation and ablation areas of the front and rear surfaces of the aluminum honeycomb increase with the increasing of the arm length of the aluminum honeycomb. At the same time, the physical quantities mentioned above have similar changes in low temperature environment. The fitting formulas, such as the relationships among perforations of the front and rear surfaces of CFRP and the arm lengths of aluminum honeycomb, and ablation area of aluminum honeycomb and the arm lengths of aluminum honeycomb are given at the given experimental conditions. The micro-morphology and damage characteristics of the panels and aluminum honeycomb are analyzed at the different locations near the impact point at high temperature.
机译:随着材料科学的快速发展,航天器的原始铝合金屏蔽结构已被夹层结构逐渐取代,碳纤维增强树脂基质复合结构与铝蜂窝状结构。为了揭示碎片造成的碎屑结构造成的损伤特性,并针对航天器在轨道操作期间交替高低温度环境的工程要求,使用CFRP /铝蜂窝芯夹层屏蔽结构作为影响目的。通过使用高温和低温系统对不同冲击速度的不同铝蜂窝臂长度的CFRP /铝蜂窝夹层结构对不同铝蜂窝臂长度的损伤特性进行研究。实验结果表明,铝蜂窝状的臂长度对CFRP /铝蜂窝夹层结构的前表面和后表面的穿孔区域几乎没有影响,但冲击速度对前后的穿孔区域具有很大的效果后面板的表面。冲击速度越低,穿孔直径越小。铝蜂窝状的前表面和后表面的变形和消融区域随着铝蜂窝状的臂长而增加。同时,上述物理量在低温环境中具有类似的变化。在给定的实验条件下给出了在给定的实验条件下给出了CFRP的前表面和铝蜂窝臂的臂长度和铝蜂窝臂的臂长度和铝蜂窝的臂长度的关系的配合公式。在高温下撞击点附近的不同位置分析面板和铝蜂窝的微观形态和损伤特性。

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