X-cor夹层结构的力学性能试验研究

X-cor夹层结构比强度高,比刚度大,有望取代传统蜂窝夹层结构作为航空航天器的主承力结构材料。采用真空固化成型工艺,通过改变Z-pin的植入参数制备了X-cor夹层结构,研究了Z-pin植入角度、植入间距和直径对其平压、剪切和拉伸性能的影响。研究结果表明,Z-pin的植入参数对X-cor夹层结构的力学性能影响显著。随Z-pin植入角度的增加X-cor夹层结构的平压性能降低,剪切性能增强,拉伸模量减小,拉伸强度先增加后减小。随Z-pin植入间距和直径增加,X-cor夹层结构力学性能均增加。与泡沫夹层结构相比,X-cor夹层结构压缩、剪切和拉伸模量的测试值分别提高了1.26～5.15倍、2.50～13.56倍和1.90～2.71倍,压缩、剪切和拉伸测试值分别提高了1.63～9.20倍、1.28～2.03倍和1.01～2.30倍。

Experimental Study on Mechanical Properties of X-cor Sandwich

X-cor sandwich has a high specific strength and specific stiffness and can be expected to replace the traditional honeycomb sandwich and become the main bearing loads structures of aircrafts.Through changing Z-pin′s inserting parameters the X-cor sandwich was prepared with vacuum curing molding process.The effects of Z-pin′s inserting angle,inserting density and diameter on compression,shear and tension properties were studied.The results show that Z-pin′s inserting parameters observably affect X-cor sandwich′s mechanical properties.The compression properties of X-cor sandwich are reduced by the increase of Z-pin′s inserting angle,and shear properties are improved by the increase of Z-pin′s inserting angle.As Z-pin′s inserting angle increase the tension modulus increases,while the tension strength firstly increases and secondly decreases.The mechanical properties increase with the increase of Z-pin′s inserting density and diameter.Compared with the foam sandwich,the experimental results of X-cor sandwich′s compression,shear and tension modulus increase by 1.26～5.15,2.50～13.56 and 1.90～2.71 times respectively,while the experimental results of compression,shear and tension strength increase by 1.63～9.20,1.28～2.03 and 1.01～2.30 times respectively.