Component e r o s i o n i n electric launcher t e c h n o l o g y( e l e c t r o m a g n e t i c EM. electrothermal ET and electrothermal-chemical ETC) plays a major role, which determines the launcher's bore lifetime, launch velocity and operational limits. The heat flux generated by the in-bore plasma leads to surface erosion because its value may exceed 100 GW/m2 over 0.1-5 ms p u l s e duration. Surface and bulk deformations will alter the mechanical properties of the launcher critical components degrading the internal ballistics and the overall performance of the launcher. A blackbody model may be sufficient to describe the heat fluxes produced by dense (1025-1026 m-3) lowtemperature(1-3eV) plasma armatures. o r electrothermal plasmas. The boundary layer (vapor shield) plasma is 'thick' to the incoming particles. Once the energy has been deposited in the boundary layer then low energy photon transport becomes the dominant mechanism by which energy is transferred to the material surface. The boundary layer thickness increases with the continuous injection of ablated material, which reduces the temperature of the boundary layer and results in less heat to the surface. Erosion studies have been conducted on the electrothermal launcher SIRENS, which simulates expected operational conditions of high heat flux deposition in electric launchers. Various material surfaces have been exposed to SIRENS plasma to test their performance, erosion behavior a n d lifetime. Tested materials are pure metals, alloys, refractory materials, specially-coated materials, insulators and composites, pure and composite graphites. Results showed that coating reduces erosion. Tungsten-based alloys have no observable erosion. Vapor shield phenomena h a s been characterized for different materials, and the energy transmission factor through the vapor s h i e l d i n g layer is obtained.