Abstract
For the future construction of the large scale space platform on the earth orbit, the structural engineering materials with the high specific strength and modulus is required to braze in space. The combination of carbon/carbon composites and titanium is one of those candidates. In the brazing process of the combination, the infiltration of the brazing filler occurs and it is harmful to the joint's characteristics. In this research, a 2-D laminated C/C composites plates with cross-ply angle of [0°/90°]S, [+45°/-45°]S and [30°/-60°]S were prepared. They were brazed to pure titanium tablet in the vacuum using the active brazing filler of Ag-32.25Cu-1.75Ti at 830℃ for 300s. The shear strength of the brazed joint was measured by the tensile shear rupture test. All of the obtained joints were fractured at the bulk C/C composites. On the case of [0°/90°] cross-ply laminated C/C composites, the shear strength reached to the maximum value up to 24MPa. The cross sections of the brazed joints were observed by optically and through SEM. The brazing filler was infiltrated along the fiber. The infiltrated brazing filler was not acted as anchors but the crack initiation points.
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