Abstract
For the future construction of the large scale space platform on the earth orbit, the high specific strength and modulus engineering materials will be required to braze in space. In this research, the combination of carbon/carbon composites and titanium is chosen and it is investigated that the effect of the cross-ply angle to the brazing interface to the shear strength and the microstructure at the brazing interface. 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°C 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 24 MPa.
