Abstract: Spread-tow fabric composites have gained prominence in aerospace applications due to their flexible design capabilities. However, the fabrication of large-scale, complex-shaped composite components inevitably requires the incorporation of joint structures to meet molding requirements. Compared to conventional thickness fabrics, expanded fabrics exhibit the characteristic features of “single-layer thinness and large grid spacing.” The failure mechanisms within their fault-line splicing structures are more complex. This study investigates the tensile properties of spread-tow fabric composites laminates containing fault-spliced plies. Furthermore, full-field strain distributions and fracture morphologies were characterized via Digital Image Correlation (DIC) and 3D pro-filometry to provide visual insights into the failure process. The results indicate that as the splicing distance in-creases from 0 mm to 48 mm, the tensile strength improves from 1.16 GPa to 1.28 GPa, with the strength reten-tion rate rising from 82.3% to 95.6%. DIC analysis confirms that increasing the distance ef-fectively suppresses the interference and superposition of strain concentration zones induced by adjacent splic-ing points, thereby delaying the coalescence of macroscopic damage. Moreover, shifting the splicing interface toward the laminate mid-plane significantly enhances the stability of failure behavior. Comparing specimens with different splice depths, the fracture location was shifted from the surface to 1/4 of the specimen thickness. This resulted in a tensile strength increase from 1.03 GPa to 1.19 GPa, representing a 15.5% improvement and enhancing the material's damage tolerance.