Abstract: To develop carbon/epoxy electrothermal composites suitable for helicopter anti-icing/de-icing protection, this study designed and fabricated three types of electrothermal fabrics containing Cr20Ni80 alloy wires based on a customized fiber stitching process. These fabrics were used as the middle layer of symmetrically laminated composites with carbon fiber satin fabrics. When energized at a voltage range of 4.9 V-6.3 V for 20 seconds, the surface temperature of all three electrothermal compo-sites could rise to above 50℃. The results showed that after incorporating the electrothermal layer, the retention rates of warp and weft interlaminar shear strength (ILSS) of the three carbon/epoxy electrothermal composites reached over 88.9% and 84.9%, respectively, with the main failure mode being interfacial delamination between the electrothermal layer and the epoxy resin matrix. When continuously energized at a power density of 0.3 W/cm² for 20 seconds, the retention rates of warp and weft ILSS of the three electrothermal composites were over 93.1% and 91.5% compared with the non-energized state; when energized at a power density of 0.5 W/cm² for 60 seconds, the retention rates of warp and weft ILSS were over 69% and 73.6% respectively relative to the non-energized state. Under energized shear loading, the failure modes of the carbon/epoxy electrothermal composites are manifested as three types: interfacial delamination between the electrothermal layer and the epoxy resin matrix, carbon fiber fracture and matrix cracking.